data/extended.jsonl

{"task_id": "extended:ERCOFTA_pump/1", "track": "extended", "case_id": "ERCOFTA_pump/1", "family": "ERCOFTA_pump", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a steady incompressible ERCOFTA pump reference case using OpenFOAM-13 with foamRun -solver incompressibleFluid, using the tutorial-style MRF rotating-machine setup with a rotor cellZone, inlet/outlet boundaries, and wall patches for the blade and shroud surfaces. Keep the design-speed rotation rate and the baseline RANS closure fixed. Run from t=0 to t=0.001 with deltaT=5e-7 and write every time step. Treat this as the supplied rectangular rotating-region surrogate, not as an unspecified blade-resolved pump: the domain is 0.6 x 0.25 x 0.2 m, and the baseline rotor zone occupies x=0 to 0.3 m. Use angular velocity -20 rad/s about the z-axis. Use an incompressible liquid with kinematic viscosity 1e-6 m2/s, a volumetric inlet flow of 0.03473 m3/s and zero-gauge outlet pressure. Preserve the rotating and stationary wall roles.", "external_asset_ids": []}
{"task_id": "extended:ERCOFTA_pump/10", "track": "extended", "case_id": "ERCOFTA_pump/10", "family": "ERCOFTA_pump", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a steady compressible ERCOFTA rotating-machine surrogate using foamRun -solver fluid. Change only the uniform rectangular surrogate mesh from 24x8x16 to 48x16x32; retain omega=-20, RAS kOmegaSST, thermophysical fields, boundaries, steady discretisation, and run controls. This is the fine-mesh resolution variant, not a claim of supplied double-row blade geometry. Treat this as the supplied rectangular rotating-region surrogate, not as an unspecified blade-resolved pump: the domain is 0.6 x 0.25 x 0.2 m, and the baseline rotor zone occupies x=0 to 0.3 m. Use angular velocity -20 rad/s about the z-axis. Use calorically perfect air at 300 K with molecular weight 28.964, Cp=1004.7 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.72; set the inlet mass flow rate to 0.03473 kg/s and the outlet pressure to 101325 Pa. Preserve the rotating and stationary wall roles.", "external_asset_ids": []}
{"task_id": "extended:ERCOFTA_pump/2", "track": "extended", "case_id": "ERCOFTA_pump/2", "family": "ERCOFTA_pump", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a steady compressible ERCOFTA pump reference case using OpenFOAM-13 with foamRun -solver fluid, keeping the tutorial-style rotating-region setup, the rotor cellZone, inlet/outlet boundaries, and the baseline RANS closure fixed. Retain the compressible thermophysical settings and the design-speed rotation rate. Run from t=0 to t=0.001 with deltaT=5e-7 and write every time step. Treat this as the supplied rectangular rotating-region surrogate, not as an unspecified blade-resolved pump: the domain is 0.6 x 0.25 x 0.2 m, and the baseline rotor zone occupies x=0 to 0.3 m. Use angular velocity -20 rad/s about the z-axis. Use calorically perfect air at 300 K with molecular weight 28.964, Cp=1004.7 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.72; set the inlet mass flow rate to 0.03473 kg/s and the outlet pressure to 101325 Pa. Preserve the rotating and stationary wall roles.", "external_asset_ids": []}
{"task_id": "extended:ERCOFTA_pump/3", "track": "extended", "case_id": "ERCOFTA_pump/3", "family": "ERCOFTA_pump", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a steady ERCOFTA pump case using OpenFOAM-13 with foamRun -solver fluid, following the same tutorial-derived rotating-region setup as the baseline but changing only the rotating speed away from the design RPM. Keep the rotor cellZone, boundary layout, turbulence model, and all other settings fixed. Run from t=0 to t=0.001 with deltaT=5e-7 and write every time step. Treat this as the supplied rectangular rotating-region surrogate, not as an unspecified blade-resolved pump: the domain is 0.6 x 0.25 x 0.2 m, and the baseline rotor zone occupies x=0 to 0.3 m. Use angular velocity -25 rad/s about the z-axis. Use calorically perfect air at 300 K with molecular weight 28.964, Cp=1004.7 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.72; set the inlet mass flow rate to 0.03473 kg/s and the outlet pressure to 101325 Pa. Preserve the rotating and stationary wall roles.", "external_asset_ids": []}
{"task_id": "extended:ERCOFTA_pump/4", "track": "extended", "case_id": "ERCOFTA_pump/4", "family": "ERCOFTA_pump", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform the steady compressible ERCOFTA rotating-region surrogate with foamRun -solver fluid and change only the OUTLET fixed pressure from the 101325 Pa baseline to 120000 Pa. Keep the rotor cellZone, omega=-20, kOmegaSST, thermophysical model, mesh, boundaries, steady SIMPLE settings, endTime=0.001, deltaT=5e-7, and writeInterval=1 fixed. Treat this as the supplied rectangular rotating-region surrogate, not as an unspecified blade-resolved pump: the domain is 0.6 x 0.25 x 0.2 m, and the baseline rotor zone occupies x=0 to 0.3 m. Use angular velocity -20 rad/s about the z-axis. Use calorically perfect air at 300 K with molecular weight 28.964, Cp=1004.7 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.72; set the inlet mass flow rate to 0.03473 kg/s and the outlet pressure to 120000 Pa. Preserve the rotating and stationary wall roles.", "external_asset_ids": []}
{"task_id": "extended:ERCOFTA_pump/5", "track": "extended", "case_id": "ERCOFTA_pump/5", "family": "ERCOFTA_pump", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a transient compressible ERCOFTA rotating-region surrogate using foamRun -solver fluid with the same perfect-gas thermophysical model, inlet/outlet conditions, U field, omega=-20, mesh, and rotor cellZone as the compressible baseline. Change only the temporal/turbulence treatment to Euler + PIMPLE with LES kOmegaSSTDES; use endTime=0.001, deltaT=1e-6, and writeInterval=1. Treat this as the supplied rectangular rotating-region surrogate, not as an unspecified blade-resolved pump: the domain is 0.6 x 0.25 x 0.2 m, and the baseline rotor zone occupies x=0 to 0.3 m. Use angular velocity -20 rad/s about the z-axis. Use calorically perfect air at 300 K with molecular weight 28.964, Cp=1004.7 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.72; set the inlet mass flow rate to 0.03473 kg/s and the outlet pressure to 101325 Pa. Preserve the rotating and stationary wall roles.", "external_asset_ids": []}
{"task_id": "extended:ERCOFTA_pump/6", "track": "extended", "case_id": "ERCOFTA_pump/6", "family": "ERCOFTA_pump", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a steady ERCOFTA pump case using OpenFOAM-13 with foamRun -solver fluid, following the same tutorial-derived rotating-region setup as the baseline but switching only the turbulence model to kEpsilon. Keep the rotor cellZone, rotating speed, and all other settings fixed. Run from t=0 to t=0.001 with deltaT=5e-7 and write every time step. Treat this as the supplied rectangular rotating-region surrogate, not as an unspecified blade-resolved pump: the domain is 0.6 x 0.25 x 0.2 m, and the baseline rotor zone occupies x=0 to 0.3 m. Use angular velocity -20 rad/s about the z-axis. Use calorically perfect air at 300 K with molecular weight 28.964, Cp=1004.7 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.72; set the inlet mass flow rate to 0.03473 kg/s and the outlet pressure to 101325 Pa. Preserve the rotating and stationary wall roles.", "external_asset_ids": []}
{"task_id": "extended:ERCOFTA_pump/7", "track": "extended", "case_id": "ERCOFTA_pump/7", "family": "ERCOFTA_pump", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a steady compressible ERCOFTA rotating-region surrogate with foamRun -solver fluid as a rotor-zone-extent sensitivity case. Extend only the boxToCell rotor region from the baseline x=0..0.3 to x=0..0.45 while retaining omega=-20, RAS kOmegaSST, thermophysical fields, mesh, boundary conditions, steady SIMPLE settings, endTime=0.001, deltaT=5e-7, and writeInterval=1. Treat this as the supplied rectangular rotating-region surrogate, not as an unspecified blade-resolved pump: the domain is 0.6 x 0.25 x 0.2 m, and the baseline rotor zone occupies x=0 to 0.3 m. Use angular velocity -20 rad/s about the z-axis. Use calorically perfect air at 300 K with molecular weight 28.964, Cp=1004.7 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.72; set the inlet mass flow rate to 0.03473 kg/s and the outlet pressure to 101325 Pa. Preserve the rotating and stationary wall roles.", "external_asset_ids": []}
{"task_id": "extended:ERCOFTA_pump/8", "track": "extended", "case_id": "ERCOFTA_pump/8", "family": "ERCOFTA_pump", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a steady compressible ERCOFTA rotating-region surrogate using foamRun -solver fluid with omega=-15, retaining the baseline kOmegaSST, perfect-gas thermophysical model, rotor zone, mesh, boundaries, steady SIMPLE controls, and post-processing. This is the low-speed companion to omega=-20 baseline and omega=-25 variant. Treat this as the supplied rectangular rotating-region surrogate, not as an unspecified blade-resolved pump: the domain is 0.6 x 0.25 x 0.2 m, and the baseline rotor zone occupies x=0 to 0.3 m. Use angular velocity -15 rad/s about the z-axis. Use calorically perfect air at 300 K with molecular weight 28.964, Cp=1004.7 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.72; set the inlet mass flow rate to 0.03473 kg/s and the outlet pressure to 101325 Pa. Preserve the rotating and stationary wall roles.", "external_asset_ids": []}
{"task_id": "extended:ERCOFTA_pump/9", "track": "extended", "case_id": "ERCOFTA_pump/9", "family": "ERCOFTA_pump", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a transient ERCOFTA pump case using OpenFOAM-13 with foamRun -solver fluid, following the same tutorial-derived rotating-machinery setup as the baseline but using the legacy rhoPimpleFoam-style transient PIMPLE coupling. Keep the rotor cellZone, rotating speed, turbulence model, and all other settings fixed. Run from t=0 to t=0.001 with deltaT=5e-7 and write every time step. Treat this as the supplied rectangular rotating-region surrogate, not as an unspecified blade-resolved pump: the domain is 0.6 x 0.25 x 0.2 m, and the baseline rotor zone occupies x=0 to 0.3 m. Use angular velocity -20 rad/s about the z-axis. Use calorically perfect air at 300 K with molecular weight 28.964, Cp=1004.7 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.72; set the inlet mass flow rate to 0.03473 kg/s and the outlet pressure to 101325 Pa. Preserve the rotating and stationary wall roles.", "external_asset_ids": []}
{"task_id": "extended:MRF_stirredReactor/1", "track": "extended", "case_id": "MRF_stirredReactor/1", "family": "MRF_stirredReactor", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform an incompressible laminar stirred-reactor benchmark using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to a steady simpleFoam-style MRF calculation. Use a tutorial-derived Rushton stirred tank setup with the tank, shaft, impeller/stirrer, rotating zone, and stationary baffles where applicable. Configure a rotating MRF cellZone for the impeller region at 100 rpm. Use a Newtonian fluid with constant kinematic viscosity and laminar momentum transport. Run steady-state SIMPLE iterations from t=0 to t=1000 with deltaT=1 and write results every 100 time steps. Include stirrer torque or power monitoring when supported by the tutorial-derived setup. Use the supplied Rushton geometry assets (simpleRushtonMRF/stirrer4, simpleRushtonMRF/stirrer6, simpleRushtonMRF/baffles) rather than inventing a different impeller. The tank diameter is 1.0 m, its height is 1.2 m, the impeller radius is 0.15 m and the rotating-zone radius is 0.20 m. Use a Newtonian liquid with kinematic viscosity 1e-6 m2/s. Maintain a small through-flow with mean inlet velocity 1e-3 m/s and an open pressure outlet. Keep the tank, shaft, impeller and baffle surfaces no-slip except where the selected rotating-frame formulation requires otherwise.", "external_asset_ids": ["simpleRushtonMRF/stirrer4", "simpleRushtonMRF/stirrer6", "simpleRushtonMRF/baffles"]}
{"task_id": "extended:MRF_stirredReactor/10", "track": "extended", "case_id": "MRF_stirredReactor/10", "family": "MRF_stirredReactor", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a two-phase liquid-liquid stirred-reactor MRF benchmark using water and oil with incompressibleVoF. Initialise a finite oil layer over a water region using OpenFOAM-13 setFields syntax, use zero gravity and retain p_rgh, interface compression, adaptive time stepping, and a 100 rpm MRF rotor. This is the water/oil variant, distinct from the single-phase laminar, turbulence, baffle, rheology, NCC, and transient variants. Use an eight-sector rotor-stator vessel with outer radius 0.10 m, rotor-tip radius 0.05 m, stator-tip radius 0.07 m and a 0.01 m quasi-2D thickness. Water has density 1000 kg/m3 and kinematic viscosity 1e-4 m2/s; oil has density 500 kg/m3 and the same viscosity; surface tension is 0.05 N/m and gravity is zero. Initially the lower portion up to z=0.0025 m is water and the rest is oil.", "external_asset_ids": []}
{"task_id": "extended:MRF_stirredReactor/2", "track": "extended", "case_id": "MRF_stirredReactor/2", "family": "MRF_stirredReactor", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform an incompressible turbulent stirred-reactor benchmark using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to a steady simpleFoam-style MRF calculation. Use the tutorial-derived Rushton stirred tank geometry with a rotating MRF cellZone for the impeller region and stationary tank/baffle walls. Set the impeller speed to 100 rpm. Use a Newtonian fluid with constant kinematic viscosity and the RAS kEpsilon turbulence model. Run steady-state SIMPLE iterations from t=0 to t=1000 with deltaT=1 and write results every 100 time steps. Include stirrer torque or power monitoring when supported by the tutorial-derived setup. Use the supplied Rushton geometry assets (simpleRushtonMRF/stirrer4, simpleRushtonMRF/stirrer6, simpleRushtonMRF/baffles) rather than inventing a different impeller. The tank diameter is 1.0 m, its height is 1.2 m, the impeller radius is 0.15 m and the rotating-zone radius is 0.20 m. Use a Newtonian liquid with kinematic viscosity 1e-6 m2/s. Maintain a small through-flow with mean inlet velocity 1e-3 m/s and an open pressure outlet. Keep the tank, shaft, impeller and baffle surfaces no-slip except where the selected rotating-frame formulation requires otherwise.", "external_asset_ids": ["simpleRushtonMRF/stirrer4", "simpleRushtonMRF/stirrer6", "simpleRushtonMRF/baffles"]}
{"task_id": "extended:MRF_stirredReactor/3", "track": "extended", "case_id": "MRF_stirredReactor/3", "family": "MRF_stirredReactor", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform an incompressible turbulent stirred-reactor benchmark using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to a steady simpleFoam-style MRF calculation. Use the same tutorial-derived Rushton stirred tank geometry and rotating MRF cellZone as the kEpsilon baseline. Set the impeller speed to 100 rpm. Use a Newtonian fluid with constant kinematic viscosity and the RAS kOmegaSST turbulence model. Run steady-state SIMPLE iterations from t=0 to t=1000 with deltaT=1 and write results every 100 time steps. Keep the mesh, boundary conditions, and MRF rotating-zone setup consistent with the kEpsilon case so the turbulence-model effect can be compared. Use the supplied Rushton geometry assets (simpleRushtonMRF/stirrer4, simpleRushtonMRF/stirrer6, simpleRushtonMRF/baffles) rather than inventing a different impeller. The tank diameter is 1.0 m, its height is 1.2 m, the impeller radius is 0.15 m and the rotating-zone radius is 0.20 m. Use a Newtonian liquid with kinematic viscosity 1e-6 m2/s. Maintain a small through-flow with mean inlet velocity 1e-3 m/s and an open pressure outlet. Keep the tank, shaft, impeller and baffle surfaces no-slip except where the selected rotating-frame formulation requires otherwise.", "external_asset_ids": ["simpleRushtonMRF/stirrer4", "simpleRushtonMRF/stirrer6", "simpleRushtonMRF/baffles"]}
{"task_id": "extended:MRF_stirredReactor/4", "track": "extended", "case_id": "MRF_stirredReactor/4", "family": "MRF_stirredReactor", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform an incompressible stirred-reactor MRF speed-sensitivity benchmark using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to steady simpleFoam-style calculations. Use the tutorial-derived Rushton stirred tank geometry with a rotating MRF cellZone and stationary tank/baffle walls. Use a Newtonian fluid with constant kinematic viscosity and the RAS kEpsilon turbulence model. Run an impeller-speed comparison for 50 rpm, 100 rpm, and 200 rpm by changing the rotating-zone omega value while keeping the mesh, boundary conditions, and numerical schemes fixed. Run each speed case from t=0 to t=1000 with deltaT=1 and write results every 100 time steps. Use the supplied Rushton geometry assets (simpleRushtonMRF/stirrer4, simpleRushtonMRF/stirrer6, simpleRushtonMRF/baffles) rather than inventing a different impeller. The tank diameter is 1.0 m, its height is 1.2 m, the impeller radius is 0.15 m and the rotating-zone radius is 0.20 m. Use a Newtonian liquid with kinematic viscosity 1e-6 m2/s. Maintain a small through-flow with mean inlet velocity 1e-3 m/s and an open pressure outlet. Keep the tank, shaft, impeller and baffle surfaces no-slip except where the selected rotating-frame formulation requires otherwise.", "external_asset_ids": ["simpleRushtonMRF/stirrer4", "simpleRushtonMRF/stirrer6", "simpleRushtonMRF/baffles"]}
{"task_id": "extended:MRF_stirredReactor/5", "track": "extended", "case_id": "MRF_stirredReactor/5", "family": "MRF_stirredReactor", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform an incompressible stirred-reactor MRF baffle-sensitivity benchmark using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to steady simpleFoam-style calculations. Use the tutorial-derived Rushton stirred tank setup and compare a baffled tank configuration with four stationary baffles against an otherwise identical unbaffled tank configuration. Use the same rotating MRF cellZone, impeller geometry, Newtonian constant-viscosity fluid, 100 rpm impeller speed, and RAS kEpsilon turbulence model in both configurations. Run each case from t=0 to t=1000 with deltaT=1 and write results every 100 time steps so the baffle effect on flow and stirrer power can be compared. Use the supplied Rushton geometry assets (simpleRushtonMRF/stirrer4, simpleRushtonMRF/stirrer6, simpleRushtonMRF/baffles) rather than inventing a different impeller. The tank diameter is 1.0 m, its height is 1.2 m, the impeller radius is 0.15 m and the rotating-zone radius is 0.20 m. Use a Newtonian liquid with kinematic viscosity 1e-6 m2/s. Maintain a small through-flow with mean inlet velocity 1e-3 m/s and an open pressure outlet. Keep the tank, shaft, impeller and baffle surfaces no-slip except where the selected rotating-frame formulation requires otherwise.", "external_asset_ids": ["simpleRushtonMRF/stirrer4", "simpleRushtonMRF/stirrer6", "simpleRushtonMRF/baffles"]}
{"task_id": "extended:MRF_stirredReactor/6", "track": "extended", "case_id": "MRF_stirredReactor/6", "family": "MRF_stirredReactor", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform an incompressible stirred-reactor MRF benchmark for a polymer-like non-Newtonian liquid using OpenFOAM-13 with foamRun -solver incompressibleFluid. Use the tutorial-derived Rushton stirred tank geometry with the rotating MRF cellZone, impeller, shaft, and baffles. Configure a generalised-Newtonian CrossPowerLaw viscosity model for the liquid instead of a constant-viscosity Newtonian model. Use an impeller speed of 100 rpm and a steady simpleFoam-style MRF formulation. Run from t=0 to t=1000 with deltaT=1 and write results every 100 time steps. Keep the mesh and boundary conditions consistent with the Newtonian MRF baseline so the rheology effect can be compared. Use the supplied Rushton geometry assets (simpleRushtonMRF/stirrer4, simpleRushtonMRF/stirrer6, simpleRushtonMRF/baffles) rather than inventing a different impeller. The tank diameter is 1.0 m, its height is 1.2 m, the impeller radius is 0.15 m and the rotating-zone radius is 0.20 m. For the non-Newtonian variant use the Cross-Power-Law values nu0=0.01 m2/s, nuInf=10 m2/s, m=0.4 s and n=3. Maintain a small through-flow with mean inlet velocity 1e-3 m/s and an open pressure outlet. Keep the tank, shaft, impeller and baffle surfaces no-slip except where the selected rotating-frame formulation requires otherwise.", "external_asset_ids": ["simpleRushtonMRF/stirrer4", "simpleRushtonMRF/stirrer6", "simpleRushtonMRF/baffles"]}
{"task_id": "extended:MRF_stirredReactor/7", "track": "extended", "case_id": "MRF_stirredReactor/7", "family": "MRF_stirredReactor", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a stirred-reactor comparison between a steady MRF approximation and a sliding-mesh/NCC rotating-impeller calculation using OpenFOAM-13 with foamRun -solver incompressibleFluid. Use tutorial-derived Rushton stirred tank setups for both cases, keeping the tank, baffles, impeller geometry, fluid properties, turbulence model, and impeller speed consistent. For the MRF case, use the rotating MRF cellZone formulation. For the sliding-mesh case, use the corresponding non-conformal coupling or dynamic-mesh tutorial workflow for the rotating impeller region. Use a Newtonian fluid, an impeller speed of 100 rpm, and the RAS kEpsilon turbulence model. Compare the resulting flow field and stirrer power or torque outputs. Extend the full run to t=100 with writeInterval=10 so the sliding-mesh power reaches a stable endpoint. Use the supplied Rushton geometry assets (simpleRushtonMRF/stirrer4, simpleRushtonMRF/stirrer6, simpleRushtonMRF/baffles) rather than inventing a different impeller. The tank diameter is 1.0 m, its height is 1.2 m, the impeller radius is 0.15 m and the rotating-zone radius is 0.20 m. Use a Newtonian liquid with kinematic viscosity 1e-6 m2/s. Maintain a small through-flow with mean inlet velocity 1e-3 m/s and an open pressure outlet. Keep the tank, shaft, impeller and baffle surfaces no-slip except where the selected rotating-frame formulation requires otherwise.", "external_asset_ids": ["simpleRushtonMRF/stirrer4", "simpleRushtonMRF/stirrer6", "simpleRushtonMRF/baffles"]}
{"task_id": "extended:MRF_stirredReactor/8", "track": "extended", "case_id": "MRF_stirredReactor/8", "family": "MRF_stirredReactor", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a steady incompressible stirred-reactor MRF mesh-refinement benchmark using foamRun -solver incompressibleFluid with RAS kEpsilon, 100 rpm, the same Rushton geometry, baffles, fluid properties, steady controls, power functions, and boundary conditions as the baseline. Change only the structured tank mesh factor from 1 to 2. Use the supplied Rushton geometry assets (simpleRushtonMRF/stirrer4, simpleRushtonMRF/stirrer6, simpleRushtonMRF/baffles) rather than inventing a different impeller. The tank diameter is 1.0 m, its height is 1.2 m, the impeller radius is 0.15 m and the rotating-zone radius is 0.20 m. Use a Newtonian liquid with kinematic viscosity 1e-6 m2/s. Maintain a small through-flow with mean inlet velocity 1e-3 m/s and an open pressure outlet. Keep the tank, shaft, impeller and baffle surfaces no-slip except where the selected rotating-frame formulation requires otherwise.", "external_asset_ids": ["simpleRushtonMRF/stirrer4", "simpleRushtonMRF/stirrer6", "simpleRushtonMRF/baffles"]}
{"task_id": "extended:MRF_stirredReactor/9", "track": "extended", "case_id": "MRF_stirredReactor/9", "family": "MRF_stirredReactor", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a transient incompressible stirred-reactor MRF benchmark using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to the legacy pimpleFoam application. Use the same tutorial-derived Rushton stirred tank geometry and rotating MRF cellZone as the steady MRF baseline. Use a Newtonian fluid with constant kinematic viscosity, an impeller speed of 100 rpm, and the RAS kEpsilon turbulence model. Use transient time discretisation with PIMPLE pressure-velocity coupling instead of steady SIMPLE. Run from t=0 to t=1 with deltaT=0.001 and write results every 100 time steps. Keep the mesh, boundary conditions, and MRF rotating-zone setup consistent with the steady MRF case. Use the supplied Rushton geometry assets (simpleRushtonMRF/stirrer4, simpleRushtonMRF/stirrer6, simpleRushtonMRF/baffles) rather than inventing a different impeller. The tank diameter is 1.0 m, its height is 1.2 m, the impeller radius is 0.15 m and the rotating-zone radius is 0.20 m. Use a Newtonian liquid with kinematic viscosity 1e-6 m2/s. Maintain a small through-flow with mean inlet velocity 1e-3 m/s and an open pressure outlet. Keep the tank, shaft, impeller and baffle surfaces no-slip except where the selected rotating-frame formulation requires otherwise.", "external_asset_ids": ["simpleRushtonMRF/stirrer4", "simpleRushtonMRF/stirrer6", "simpleRushtonMRF/baffles"]}
{"task_id": "extended:aerofoilNACA0012/1", "track": "extended", "case_id": "aerofoilNACA0012/1", "family": "aerofoilNACA0012", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a low-subsonic NACA0012 aerofoil benchmark using OpenFOAM-13 with foamRun -solver fluid. Use the provided NACA0012 aerofoil geometry for mesh generation. The target condition is Ma=0.15 at zero angle of attack; set speed=52 m/s and angleOfAttack=0 degrees in 0/U. Use the kOmegaSST RANS turbulence model and the standard projected NACA0012 mesh with extruded front/back constraint patches. Run from t=0 to t=500; deltaT=1; write results every 50 time steps using writeControl=timeStep. Include the OpenFOAM case configuration, initial and boundary fields, mesh dictionaries, force coefficient function object, and the external geometry path needed to run the case. Treat the supplied NACA0012 surface as a unit-chord aerofoil. Use calorically perfect air at 298 K and 100000 Pa with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.82e-5 Pa s and Pr=0.71; impose a no-slip aerofoil and far-field conditions. Use a 1 m reference chord and unit reference span for force coefficients.", "external_asset_ids": ["naca0012/NACA0012"]}
{"task_id": "extended:aerofoilNACA0012/10", "track": "extended", "case_id": "aerofoilNACA0012/10", "family": "aerofoilNACA0012", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a steady compressible NACA0012 aerofoil turbulence variant using foamRun -solver fluid with the 2D structured/snappy geometry, SpalartAllmaras RAS, steady SIMPLE controls, and the same Mach 0.5, AoA=0, mesh, thermophysical fields, and forceCoeffs workflow as the baseline. This is the economical 2D SA-RANS alternative to the baseline kOmegaSST case; it does not claim DDES. Treat the supplied NACA0012 surface as a unit-chord aerofoil. Use calorically perfect air at 298 K and 100000 Pa with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.82e-5 Pa s and Pr=0.71; impose a no-slip aerofoil and far-field conditions. Use a 1 m reference chord and unit reference span for force coefficients.", "external_asset_ids": ["naca0012/NACA0012"]}
{"task_id": "extended:aerofoilNACA0012/2", "track": "extended", "case_id": "aerofoilNACA0012/2", "family": "aerofoilNACA0012", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a subsonic NACA0012 aerofoil benchmark using OpenFOAM-13 with foamRun -solver fluid. Use the provided NACA0012 aerofoil geometry for mesh generation. The target condition is Ma=0.5 at zero angle of attack; set speed=173 m/s and angleOfAttack=0 degrees in 0/U. Use the kOmegaSST RANS turbulence model and the standard projected NACA0012 mesh with extruded front/back constraint patches. Run from t=0 to t=500; deltaT=1; write results every 50 time steps using writeControl=timeStep. Include the OpenFOAM case configuration, initial and boundary fields, mesh dictionaries, force coefficient function object, and the external geometry path needed to run the case. Treat the supplied NACA0012 surface as a unit-chord aerofoil. Use calorically perfect air at 298 K and 100000 Pa with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.82e-5 Pa s and Pr=0.71; impose a no-slip aerofoil and far-field conditions. Use a 1 m reference chord and unit reference span for force coefficients.", "external_asset_ids": ["naca0012/NACA0012"]}
{"task_id": "extended:aerofoilNACA0012/3", "track": "extended", "case_id": "aerofoilNACA0012/3", "family": "aerofoilNACA0012", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a transonic-onset NACA0012 aerofoil benchmark using OpenFOAM-13 with foamRun -solver fluid. Use the provided NACA0012 aerofoil geometry for mesh generation. The target condition is Ma=0.7 at zero angle of attack; set speed=242 m/s and angleOfAttack=0 degrees in 0/U. Use the kOmegaSST RANS turbulence model and the standard projected NACA0012 mesh with extruded front/back constraint patches. Run from t=0 to t=500; deltaT=1; write results every 50 time steps using writeControl=timeStep. Include the OpenFOAM case configuration, initial and boundary fields, mesh dictionaries, force coefficient function object, and the external geometry path needed to run the case. Treat the supplied NACA0012 surface as a unit-chord aerofoil. Use calorically perfect air at 298 K and 100000 Pa with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.82e-5 Pa s and Pr=0.71; impose a no-slip aerofoil and far-field conditions. Use a 1 m reference chord and unit reference span for force coefficients.", "external_asset_ids": ["naca0012/NACA0012"]}
{"task_id": "extended:aerofoilNACA0012/4", "track": "extended", "case_id": "aerofoilNACA0012/4", "family": "aerofoilNACA0012", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a transonic NACA0012 aerofoil benchmark using OpenFOAM-13 with foamRun -solver fluid. Use the provided NACA0012 aerofoil geometry for mesh generation. The target condition is Ma=0.8 at zero angle of attack; set speed=277 m/s and angleOfAttack=0 degrees in 0/U. Use the kOmegaSST RANS turbulence model and the standard projected NACA0012 mesh with extruded front/back constraint patches. Run from t=0 to t=500; deltaT=1; write results every 50 time steps using writeControl=timeStep. Include the OpenFOAM case configuration, initial and boundary fields, mesh dictionaries, force coefficient function object, and the external geometry path needed to run the case. Treat the supplied NACA0012 surface as a unit-chord aerofoil. Use calorically perfect air at 298 K and 100000 Pa with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.82e-5 Pa s and Pr=0.71; impose a no-slip aerofoil and far-field conditions. Use a 1 m reference chord and unit reference span for force coefficients.", "external_asset_ids": ["naca0012/NACA0012"]}
{"task_id": "extended:aerofoilNACA0012/5", "track": "extended", "case_id": "aerofoilNACA0012/5", "family": "aerofoilNACA0012", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a negative-five-degree NACA0012 aerofoil benchmark using OpenFOAM-13 with foamRun -solver fluid. Use the provided NACA0012 aerofoil geometry for mesh generation. The target angle condition is AoA=-5 degrees at Ma=0.5; set speed=173 m/s and angleOfAttack=-5 degrees in 0/U. Use the kOmegaSST RANS turbulence model and the standard projected NACA0012 mesh with extruded front/back constraint patches. Run from t=0 to t=500; deltaT=1; write results every 50 time steps using writeControl=timeStep. Include the OpenFOAM case configuration, initial and boundary fields, mesh dictionaries, force coefficient function object, and the external geometry path needed to run the case. Treat the supplied NACA0012 surface as a unit-chord aerofoil. Use calorically perfect air at 298 K and 100000 Pa with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.82e-5 Pa s and Pr=0.71; impose a no-slip aerofoil and far-field conditions. Use a 1 m reference chord and unit reference span for force coefficients.", "external_asset_ids": ["naca0012/NACA0012"]}
{"task_id": "extended:aerofoilNACA0012/6", "track": "extended", "case_id": "aerofoilNACA0012/6", "family": "aerofoilNACA0012", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a five-degree angle-of-attack NACA0012 aerofoil benchmark using OpenFOAM-13 with foamRun -solver fluid. Use the provided NACA0012 aerofoil geometry for mesh generation. The target angle condition is AoA=5 degrees at Ma=0.5; set speed=173 m/s and angleOfAttack=5 degrees in 0/U. Use the kOmegaSST RANS turbulence model and the standard projected NACA0012 mesh with extruded front/back constraint patches. Run from t=0 to t=1000; deltaT=1; write results every 50 time steps using writeControl=timeStep. Include the OpenFOAM case configuration, initial and boundary fields, mesh dictionaries, force coefficient function object, and the external geometry path needed to run the case. Treat the supplied NACA0012 surface as a unit-chord aerofoil. Use calorically perfect air at 298 K and 100000 Pa with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.82e-5 Pa s and Pr=0.71; impose a no-slip aerofoil and far-field conditions. Use a 1 m reference chord and unit reference span for force coefficients.", "external_asset_ids": ["naca0012/NACA0012"]}
{"task_id": "extended:aerofoilNACA0012/7", "track": "extended", "case_id": "aerofoilNACA0012/7", "family": "aerofoilNACA0012", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a ten-degree angle-of-attack NACA0012 aerofoil benchmark using OpenFOAM-13 with foamRun -solver fluid. Use the provided NACA0012 aerofoil geometry for mesh generation. The target angle condition is AoA=10 degrees at Ma=0.5; set speed=173 m/s and angleOfAttack=10 degrees in 0/U. Use the kOmegaSST RANS turbulence model and the standard projected NACA0012 mesh with extruded front/back constraint patches. Run from t=0 to t=1500; deltaT=1; write results every 50 time steps using writeControl=timeStep. Include the OpenFOAM case configuration, initial and boundary fields, mesh dictionaries, force coefficient function object, and the external geometry path needed to run the case. Treat the supplied NACA0012 surface as a unit-chord aerofoil. Use calorically perfect air at 298 K and 100000 Pa with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.82e-5 Pa s and Pr=0.71; impose a no-slip aerofoil and far-field conditions. Use a 1 m reference chord and unit reference span for force coefficients.", "external_asset_ids": ["naca0012/NACA0012"]}
{"task_id": "extended:aerofoilNACA0012/8", "track": "extended", "case_id": "aerofoilNACA0012/8", "family": "aerofoilNACA0012", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a NACA0012 aerofoil benchmark using OpenFOAM-13 with foamRun -solver fluid and a snappyHexMesh multi-level refinement strategy. Use the provided NACA0012 aerofoil geometry for mesh generation. The target condition is Ma=0.5 at AoA=0 degrees; set speed=173 m/s and angleOfAttack=0 degrees in 0/U. Use the kOmegaSST RANS turbulence model. Generate a background mesh and apply snappyHexMesh refinement around the aerofoil surface, near-field region, and downstream wake while preserving extruded front/back constraint patches for a quasi-2D aerofoil calculation. Run from t=0 to t=500; deltaT=1; write results every 50 time steps using writeControl=timeStep. Include the OpenFOAM case configuration, initial and boundary fields, blockMesh/snappyHexMesh dictionaries, force coefficient function object, and the external geometry path needed to run the case. Treat the supplied NACA0012 surface as a unit-chord aerofoil. Use calorically perfect air at 298 K and 100000 Pa with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.82e-5 Pa s and Pr=0.71; impose a no-slip aerofoil and far-field conditions. Use a 1 m reference chord and unit reference span for force coefficients.", "external_asset_ids": ["naca0012/NACA0012"]}
{"task_id": "extended:aerofoilNACA0012/9", "track": "extended", "case_id": "aerofoilNACA0012/9", "family": "aerofoilNACA0012", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a transient compressible NACA0012 aerofoil benchmark using OpenFOAM-13 with foamRun -solver fluid, corresponding to the legacy rhoPimpleFoam-style workflow. Use the provided NACA0012 aerofoil geometry for mesh generation. The target condition is Ma=0.5 at AoA=0 degrees; set speed=173 m/s and angleOfAttack=0 degrees in 0/U. Use the kOmegaSST RANS turbulence model and the standard projected NACA0012 mesh with extruded front/back constraint patches. Use transient time discretisation and PIMPLE pressure-velocity coupling suitable for the rhoPimpleFoam replacement path. Run from t=0 to t=0.15; deltaT=2e-5; write results every 0.001 simulation-time units using writeControl=adjustableRunTime. Include the OpenFOAM case configuration, initial and boundary fields, mesh dictionaries, force coefficient function object, and the external geometry path needed to run the case. Treat the supplied NACA0012 surface as a unit-chord aerofoil. Use calorically perfect air at 298 K and 100000 Pa with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.82e-5 Pa s and Pr=0.71; impose a no-slip aerofoil and far-field conditions. Use a 1 m reference chord and unit reference span for force coefficients.", "external_asset_ids": ["naca0012/NACA0012"]}
{"task_id": "extended:compressibleBubbleCollapse/1", "track": "extended", "case_id": "compressibleBubbleCollapse/1", "family": "compressibleBubbleCollapse", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible two-phase bubble-collapse benchmark using OpenFOAM-13 with foamRun -solver compressibleVoF. This is the baseline single-bubble case with a circular gas bubble of radius 50um centered in the domain at 5MPa ambient pressure, using the same 2D 10mm-high domain, water/air phases, compressible perfectFluid liquid equation of state, gamma=1.4 air, and interfaceCompression + vanLeer VOF transport as the shared baseline. Run from t=0 to t=1e-7; deltaT=1e-10; write results every 1e-8 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.3, maxAlphaCo=1, maxDeltaT=2e-9. Use a 5-degree axisymmetric wedge domain with radius and height both 10 mm. The bottom is a solid wall, the top maintains the ambient pressure and the outer radial boundary is non-penetrating. Initially the liquid and gas are at 300 K, the gas pressure is 3550 Pa, gravity is zero and surface tension is neglected. For water use the perfect-fluid relation with rho0=998 kg/m3, R=100000 J/kg and Cv=4195 J/(kg K); for the gas use a perfect-gas model with molecular weight 28.96 and Cp=1004.5 J/(kg K).", "external_asset_ids": []}
{"task_id": "extended:compressibleBubbleCollapse/10", "track": "extended", "case_id": "compressibleBubbleCollapse/10", "family": "compressibleBubbleCollapse", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible two-phase bubble-collapse benchmark using OpenFOAM-13 with foamRun -solver compressibleVoF. Change only the number of bubbles by introducing a second identical 50um bubble so the two bubbles interact, while keeping the 2D 10mm-high domain, 5MPa ambient pressure, water/air phases, compressible perfectFluid liquid equation of state, gamma=1.4 air, and interfaceCompression + vanLeer VOF transport identical to the single-bubble baseline. Run from t=0 to t=1e-7; deltaT=1e-10; write results every 1e-8 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.3, maxAlphaCo=1, maxDeltaT=2e-9. Use a 5-degree axisymmetric wedge domain with radius and height both 10 mm. The bottom is a solid wall, the top maintains the ambient pressure and the outer radial boundary is non-penetrating. Initially the liquid and gas are at 300 K, the gas pressure is 3550 Pa, gravity is zero and surface tension is neglected. For water use the perfect-fluid relation with rho0=998 kg/m3, R=100000 J/kg and Cv=4195 J/(kg K); for the gas use a perfect-gas model with molecular weight 28.96 and Cp=1004.5 J/(kg K). Place the second 50 um bubble 0.15 mm from the first in the radial direction.", "external_asset_ids": []}
{"task_id": "extended:compressibleBubbleCollapse/2", "track": "extended", "case_id": "compressibleBubbleCollapse/2", "family": "compressibleBubbleCollapse", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible two-phase bubble-collapse benchmark using OpenFOAM-13 with foamRun -solver compressibleVoF. Change only the initial gas-bubble radius, using two radius subcases of 100um and 200um, while keeping the 2D 10mm-high domain, 5MPa ambient pressure, bubble center, water/air phases, compressible perfectFluid liquid equation of state, gamma=1.4 air, and interfaceCompression + vanLeer VOF transport identical to the 50um baseline. Run from t=0 to t=1e-7; deltaT=1e-10; write results every 1e-8 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.3, maxAlphaCo=1, maxDeltaT=2e-9. Use a 5-degree axisymmetric wedge domain with radius and height both 10 mm. The bottom is a solid wall, the top maintains the ambient pressure and the outer radial boundary is non-penetrating. Initially the liquid and gas are at 300 K, the gas pressure is 3550 Pa, gravity is zero and surface tension is neglected. For water use the perfect-fluid relation with rho0=998 kg/m3, R=100000 J/kg and Cv=4195 J/(kg K); for the gas use a perfect-gas model with molecular weight 28.96 and Cp=1004.5 J/(kg K).", "external_asset_ids": []}
{"task_id": "extended:compressibleBubbleCollapse/3", "track": "extended", "case_id": "compressibleBubbleCollapse/3", "family": "compressibleBubbleCollapse", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible two-phase bubble-collapse benchmark using OpenFOAM-13 with foamRun -solver compressibleVoF. Change only the ambient pressure, using a weak-collapse branch at 2MPa and a strong-collapse branch at 10MPa, while keeping the 50um single bubble, centered placement, 2D 10mm-high domain, water/air phases, compressible perfectFluid liquid equation of state, gamma=1.4 air, and interfaceCompression + vanLeer VOF transport identical to the baseline. Run from t=0 to t=1e-7; deltaT=1e-10; write results every 1e-8 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.3, maxAlphaCo=1, maxDeltaT=2e-9. Use a 5-degree axisymmetric wedge domain with radius and height both 10 mm. The bottom is a solid wall, the top maintains the ambient pressure and the outer radial boundary is non-penetrating. Initially the liquid and gas are at 300 K, the gas pressure is 3550 Pa, gravity is zero and surface tension is neglected. For water use the perfect-fluid relation with rho0=998 kg/m3, R=100000 J/kg and Cv=4195 J/(kg K); for the gas use a perfect-gas model with molecular weight 28.96 and Cp=1004.5 J/(kg K).", "external_asset_ids": []}
{"task_id": "extended:compressibleBubbleCollapse/4", "track": "extended", "case_id": "compressibleBubbleCollapse/4", "family": "compressibleBubbleCollapse", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible two-phase bubble-collapse benchmark using OpenFOAM-13 with foamRun -solver compressibleVoF. Change only the bubble-center distance from the solid wall, placing the 50um bubble in a near-wall configuration, while keeping the 2D 10mm-high domain, 5MPa ambient pressure, water/air phases, compressible perfectFluid liquid equation of state, gamma=1.4 air, and interfaceCompression + vanLeer VOF transport identical to the baseline. Run from t=0 to t=1e-7; deltaT=1e-10; write results every 1e-8 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.3, maxAlphaCo=1, maxDeltaT=2e-9. Use a 5-degree axisymmetric wedge domain with radius and height both 10 mm. The bottom is a solid wall, the top maintains the ambient pressure and the outer radial boundary is non-penetrating. Initially the liquid and gas are at 300 K, the gas pressure is 3550 Pa, gravity is zero and surface tension is neglected. For water use the perfect-fluid relation with rho0=998 kg/m3, R=100000 J/kg and Cv=4195 J/(kg K); for the gas use a perfect-gas model with molecular weight 28.96 and Cp=1004.5 J/(kg K). Place the bubble centre 0.20 mm above the bottom wall.", "external_asset_ids": []}
{"task_id": "extended:compressibleBubbleCollapse/5", "track": "extended", "case_id": "compressibleBubbleCollapse/5", "family": "compressibleBubbleCollapse", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible two-phase bubble-collapse benchmark using OpenFOAM-13 with foamRun -solver compressibleVoF. Change only the initial gas-bubble shape, replacing the circular 50um baseline bubble with a stepped/asymmetric axis-aligned rectangular initial contour represented by two boxToCell selections at the same center location, while keeping the 2D 10mm-high domain, 5MPa ambient pressure, water/air phases, compressible perfectFluid liquid equation of state, gamma=1.4 air, and interfaceCompression + vanLeer VOF transport unchanged. Run from t=0 to t=1e-7; deltaT=1e-10; write results every 1e-8 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.3, maxAlphaCo=1, maxDeltaT=2e-9. Use a 5-degree axisymmetric wedge domain with radius and height both 10 mm. The bottom is a solid wall, the top maintains the ambient pressure and the outer radial boundary is non-penetrating. Initially the liquid and gas are at 300 K, the gas pressure is 3550 Pa, gravity is zero and surface tension is neglected. For water use the perfect-fluid relation with rho0=998 kg/m3, R=100000 J/kg and Cv=4195 J/(kg K); for the gas use a perfect-gas model with molecular weight 28.96 and Cp=1004.5 J/(kg K). Form the asymmetric bubble from two overlapping rectangles: one spanning radial coordinate -53.79 to 26.21 um and height 4.9625 to 5.0375 mm, and the second spanning 26.21 to 63.21 um and height 4.975 to 5.025 mm.", "external_asset_ids": []}
{"task_id": "extended:compressibleBubbleCollapse/6", "track": "extended", "case_id": "compressibleBubbleCollapse/6", "family": "compressibleBubbleCollapse", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible two-phase bubble-collapse benchmark using OpenFOAM-13 with foamRun -solver compressibleVoF. Change only the gas-liquid density ratio, using a lighter-gas branch by lowering the air density while keeping the liquid model, the 50um bubble geometry, the 2D 10mm-high domain, the 5MPa ambient pressure, and the interfaceCompression + vanLeer VOF transport fixed to the baseline. Run from t=0 to t=1e-7; deltaT=1e-10; write results every 1e-8 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.3, maxAlphaCo=1, maxDeltaT=2e-9. Use a 5-degree axisymmetric wedge domain with radius and height both 10 mm. The bottom is a solid wall, the top maintains the ambient pressure and the outer radial boundary is non-penetrating. Initially the liquid and gas are at 300 K, the gas pressure is 3550 Pa, gravity is zero and surface tension is neglected. For water use the perfect-fluid relation with rho0=998 kg/m3, R=100000 J/kg and Cv=4195 J/(kg K); for the gas use a perfect-gas model with molecular weight 14.48 and Cp=2009.406 J/(kg K).", "external_asset_ids": []}
{"task_id": "extended:compressibleBubbleCollapse/7", "track": "extended", "case_id": "compressibleBubbleCollapse/7", "family": "compressibleBubbleCollapse", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible two-phase bubble-collapse benchmark using OpenFOAM-13 with foamRun -solver compressibleVoF. Change only the mesh strategy by enabling AMR around the gas-liquid interface with dynamicRefineFvMesh, while keeping the 50um single bubble, 2D 10mm-high domain, 5MPa ambient pressure, water/air phases, compressible perfectFluid liquid equation of state, gamma=1.4 air, and interfaceCompression + vanLeer VOF transport identical to the baseline. Run from t=0 to t=1e-7; deltaT=1e-10; write results every 1e-8 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.3, maxAlphaCo=1, maxDeltaT=2e-9. Use a 5-degree axisymmetric wedge domain with radius and height both 10 mm. The bottom is a solid wall, the top maintains the ambient pressure and the outer radial boundary is non-penetrating. Initially the liquid and gas are at 300 K, the gas pressure is 3550 Pa, gravity is zero and surface tension is neglected. For water use the perfect-fluid relation with rho0=998 kg/m3, R=100000 J/kg and Cv=4195 J/(kg K); for the gas use a perfect-gas model with molecular weight 28.96 and Cp=1004.5 J/(kg K).", "external_asset_ids": []}
{"task_id": "extended:compressibleBubbleCollapse/8", "track": "extended", "case_id": "compressibleBubbleCollapse/8", "family": "compressibleBubbleCollapse", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform the fixed uniform fine-mesh compressible bubble-collapse baseline using foamRun -solver compressibleVoF. Keep the 50 um bubble, 5 MPa pressure, thermophysical model, interface scheme, and controls fixed while refining the uniform base mesh from 200x1x200 to 400x1x400. This is the fixed-grid resolution counterpart to the adaptive-AMR variant. Use a 5-degree axisymmetric wedge domain with radius and height both 10 mm. The bottom is a solid wall, the top maintains the ambient pressure and the outer radial boundary is non-penetrating. Initially the liquid and gas are at 300 K, the gas pressure is 3550 Pa, gravity is zero and surface tension is neglected. For water use the perfect-fluid relation with rho0=998 kg/m3, R=100000 J/kg and Cv=4195 J/(kg K); for the gas use a perfect-gas model with molecular weight 28.96 and Cp=1004.5 J/(kg K).", "external_asset_ids": []}
{"task_id": "extended:compressibleBubbleCollapse/9", "track": "extended", "case_id": "compressibleBubbleCollapse/9", "family": "compressibleBubbleCollapse", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible two-phase bubble-collapse benchmark using OpenFOAM-13 with foamRun -solver incompressibleVoF, corresponding to the legacy interFoam application. Change only the solver family and compressibility treatment for an incompressible VOF comparison, while keeping the same 50um bubble placement, 2D 10mm-high domain, water/air interface geometry, and as much of the baseline setup as the solver allows. This branch is the incompressible interFoam-style reference against the compressible bubble-collapse baseline. Run from t=0 to t=1e-7; deltaT=1e-10; write results every 1e-8 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.3, maxAlphaCo=1, maxDeltaT=2e-9. Use a 5-degree axisymmetric wedge domain with radius and height both 10 mm. The bottom is a solid wall, the top maintains the ambient pressure and the outer radial boundary is non-penetrating. Initially the liquid and gas are at 300 K, the gas pressure is 3550 Pa, gravity is zero and surface tension is neglected. For this incompressible comparison use water rho=998 kg/m3 and nu=3.653e-7 m2/s, air rho=1.2 kg/m3 and nu=1.533e-5 m2/s.", "external_asset_ids": []}
{"task_id": "extended:drivaerFastback/1", "track": "extended", "case_id": "drivaerFastback/1", "family": "drivaerFastback", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform an incompressible external-aerodynamics simulation of the DrivAer fastback model using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to the legacy simpleFoam application. DrivAer fastback baseline at 100 km/h with static ground, rotatingWallVelocity wheels, and kOmegaSST. Set Uinlet to 27.7778 m/s. Use lightweight snappy mesh level 2. Run from t=0 to t=100; deltaT=1; write results every 50 using writeControl=timeStep. Enable forceCoeffs for aerodynamic coefficients. Keep geometry referenced by DrivAer body/frontWheels/rearWheels triSurface names without embedding solver results. Use the supplied body and wheel assets (drivaerFastback/body, drivaerFastback/frontWheels, drivaerFastback/rearWheels) without altering their scale. Model air with kinematic viscosity 1.5e-5 m2/s. Use wheel radius 0.318 m and wheelbase 2.786 m; for rotating wheels set angular speed consistently from vehicle speed divided by wheel radius.", "external_asset_ids": ["drivaerFastback/body", "drivaerFastback/frontWheels", "drivaerFastback/rearWheels"]}
{"task_id": "extended:drivaerFastback/10", "track": "extended", "case_id": "drivaerFastback/10", "family": "drivaerFastback", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a transient 3D DrivAer fastback DDES benchmark using foamRun -solver incompressibleFluid with LES SpalartAllmarasDDES, Euler time discretisation, PIMPLE coupling, Uinlet=27.7778 m/s, rotating wheels, static ground, and the supplied geometry. Use endTime=10, deltaT=0.01, writeControl=timeStep, and writeInterval=10; analyse the final transient window rather than treating this as a steady simpleFoam run. Use the supplied body and wheel assets (drivaerFastback/body, drivaerFastback/frontWheels, drivaerFastback/rearWheels) without altering their scale. Model air with kinematic viscosity 1.5e-5 m2/s. Use wheel radius 0.318 m and wheelbase 2.786 m; for rotating wheels set angular speed consistently from vehicle speed divided by wheel radius.", "external_asset_ids": ["drivaerFastback/body", "drivaerFastback/frontWheels", "drivaerFastback/rearWheels"]}
{"task_id": "extended:drivaerFastback/2", "track": "extended", "case_id": "drivaerFastback/2", "family": "drivaerFastback", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Run the supplied DrivAer fastback surrogate with foamRun -solver incompressibleFluid at the baseline 27.7778 m/s, but use a 60-cell streamwise background mesh instead of 40 cells. Keep static ground, rotatingWallVelocity wheels, kOmegaSST, forceCoeffs, and run controls unchanged; this is the medium-resolution variant. For Q2 evidence, continue the validated decomposed run to t=200 and merge restart-segment forceCoeffs history. Use the supplied body and wheel assets (drivaerFastback/body, drivaerFastback/frontWheels, drivaerFastback/rearWheels) without altering their scale. Model air with kinematic viscosity 1.5e-5 m2/s. Use wheel radius 0.318 m and wheelbase 2.786 m; for rotating wheels set angular speed consistently from vehicle speed divided by wheel radius.", "external_asset_ids": ["drivaerFastback/body", "drivaerFastback/frontWheels", "drivaerFastback/rearWheels"]}
{"task_id": "extended:drivaerFastback/3", "track": "extended", "case_id": "drivaerFastback/3", "family": "drivaerFastback", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Run the supplied DrivAer fastback surrogate with foamRun -solver incompressibleFluid using the baseline Uinlet=27.7778 m/s and an 80-cell streamwise background mesh. Keep static ground, rotatingWallVelocity wheels, kOmegaSST, forceCoeffs, and run controls unchanged. This is the fine-mesh third level after the 40-cell baseline and 60-cell variant. Use the supplied body and wheel assets (drivaerFastback/body, drivaerFastback/frontWheels, drivaerFastback/rearWheels) without altering their scale. Model air with kinematic viscosity 1.5e-5 m2/s. Use wheel radius 0.318 m and wheelbase 2.786 m; for rotating wheels set angular speed consistently from vehicle speed divided by wheel radius.", "external_asset_ids": ["drivaerFastback/body", "drivaerFastback/frontWheels", "drivaerFastback/rearWheels"]}
{"task_id": "extended:drivaerFastback/4", "track": "extended", "case_id": "drivaerFastback/4", "family": "drivaerFastback", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform an incompressible external-aerodynamics simulation of the DrivAer fastback model using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to the legacy simpleFoam application. Change only the vehicle speed to 120 km/h relative to the Fastback baseline. Set Uinlet to 33.3333 m/s and compute wheelSpeed from Uinlet/wheelRadius; keep the fastback geometry, static ground, rotatingWallVelocity wheels, snappy mesh, kOmegaSST turbulence, run controls, and forceCoeffs post-processing consistent with the baseline. Use the supplied body and wheel assets (drivaerFastback/body, drivaerFastback/frontWheels, drivaerFastback/rearWheels) without altering their scale. Model air with kinematic viscosity 1.5e-5 m2/s. Use wheel radius 0.318 m and wheelbase 2.786 m; for rotating wheels set angular speed consistently from vehicle speed divided by wheel radius.", "external_asset_ids": ["drivaerFastback/body", "drivaerFastback/frontWheels", "drivaerFastback/rearWheels"]}
{"task_id": "extended:drivaerFastback/5", "track": "extended", "case_id": "drivaerFastback/5", "family": "drivaerFastback", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform an incompressible external-aerodynamics simulation of the DrivAer fastback model using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to the legacy simpleFoam application. Change only the vehicle speed to 80 km/h relative to the Fastback baseline. Set Uinlet to 22.2222 m/s and compute wheelSpeed from Uinlet/wheelRadius; keep the fastback geometry, static ground, rotatingWallVelocity wheels, snappy mesh, kOmegaSST turbulence, run controls, and forceCoeffs post-processing consistent with the baseline. Use the supplied body and wheel assets (drivaerFastback/body, drivaerFastback/frontWheels, drivaerFastback/rearWheels) without altering their scale. Model air with kinematic viscosity 1.5e-5 m2/s. Use wheel radius 0.318 m and wheelbase 2.786 m; for rotating wheels set angular speed consistently from vehicle speed divided by wheel radius.", "external_asset_ids": ["drivaerFastback/body", "drivaerFastback/frontWheels", "drivaerFastback/rearWheels"]}
{"task_id": "extended:drivaerFastback/6", "track": "extended", "case_id": "drivaerFastback/6", "family": "drivaerFastback", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform an incompressible external-aerodynamics simulation of the DrivAer fastback model using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to the legacy simpleFoam application. Change only the wheel-rotation method to an MRF-style treatment for the front and rear wheels, while keeping the fastback geometry, 100 km/h inflow, static ground, mesh setup, kOmegaSST turbulence, run controls, and forceCoeffs post-processing consistent with the baseline. Use the supplied body and wheel assets (drivaerFastback/body, drivaerFastback/frontWheels, drivaerFastback/rearWheels) without altering their scale. Model air with kinematic viscosity 1.5e-5 m2/s. Use wheel radius 0.318 m and wheelbase 2.786 m; for rotating wheels set angular speed consistently from vehicle speed divided by wheel radius.", "external_asset_ids": ["drivaerFastback/body", "drivaerFastback/frontWheels", "drivaerFastback/rearWheels"]}
{"task_id": "extended:drivaerFastback/7", "track": "extended", "case_id": "drivaerFastback/7", "family": "drivaerFastback", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform an incompressible external-aerodynamics simulation of the DrivAer fastback model using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to the legacy simpleFoam application. Change only the ground boundary condition to a moving ground with velocity Uinlet, while keeping the fastback geometry, 100 km/h inflow, rotatingWallVelocity wheels, mesh setup, kOmegaSST turbulence, run controls, and forceCoeffs post-processing consistent with the baseline. Use the supplied body and wheel assets (drivaerFastback/body, drivaerFastback/frontWheels, drivaerFastback/rearWheels) without altering their scale. Model air with kinematic viscosity 1.5e-5 m2/s. Use wheel radius 0.318 m and wheelbase 2.786 m; for rotating wheels set angular speed consistently from vehicle speed divided by wheel radius.", "external_asset_ids": ["drivaerFastback/body", "drivaerFastback/frontWheels", "drivaerFastback/rearWheels"]}
{"task_id": "extended:drivaerFastback/8", "track": "extended", "case_id": "drivaerFastback/8", "family": "drivaerFastback", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform an incompressible external-aerodynamics simulation of the DrivAer fastback model using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to the legacy simpleFoam application. Use the standard kEpsilon turbulence model, while keeping the fastback geometry, 100 km/h inflow, wheel treatment, mesh setup, run controls, and forceCoeffs post-processing consistent with the baseline. For Q2 evidence, continue the validated decomposed run to t=200 and merge restart-segment forceCoeffs history. Use the supplied body and wheel assets (drivaerFastback/body, drivaerFastback/frontWheels, drivaerFastback/rearWheels) without altering their scale. Model air with kinematic viscosity 1.5e-5 m2/s. Use wheel radius 0.318 m and wheelbase 2.786 m; for rotating wheels set angular speed consistently from vehicle speed divided by wheel radius.", "external_asset_ids": ["drivaerFastback/body", "drivaerFastback/frontWheels", "drivaerFastback/rearWheels"]}
{"task_id": "extended:drivaerFastback/9", "track": "extended", "case_id": "drivaerFastback/9", "family": "drivaerFastback", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform an incompressible external-aerodynamics simulation of the DrivAer fastback model using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to the legacy simpleFoam application. Use the standard RAS kOmega turbulence model instead of the baseline kOmegaSST model, while keeping the fastback geometry, 100 km/h inflow, wheel treatment, mesh setup, run controls, and forceCoeffs post-processing consistent with the baseline. Use the supplied body and wheel assets (drivaerFastback/body, drivaerFastback/frontWheels, drivaerFastback/rearWheels) without altering their scale. Model air with kinematic viscosity 1.5e-5 m2/s. Use wheel radius 0.318 m and wheelbase 2.786 m; for rotating wheels set angular speed consistently from vehicle speed divided by wheel radius.", "external_asset_ids": ["drivaerFastback/body", "drivaerFastback/frontWheels", "drivaerFastback/rearWheels"]}
{"task_id": "extended:nozzleCDV/1", "track": "extended", "case_id": "nozzleCDV/1", "family": "nozzleCDV", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible converging-diverging nozzle benchmark using OpenFOAM-13 with foamRun -solver fluid. CDV baseline transonic case with throat Mach number approximately 1.0. Use this as the reference structured-mesh, laminar, fluid-solver configuration. Keep the CDV geometry, structured 2D mesh, thermophysical model, laminar model, physical flow condition, and pressure-density convection format div(phi,(p|rho)) unchanged unless this variant explicitly changes that one main variable. Run as transient PIMPLE-style iterations from t=0 to t=0.005; deltaT=1e-6; write results every 0.001 simulation-time units. Use a unit-length nozzle with axial stations at x=0, 0.4, 0.6 and 1.0 m and corresponding half-heights 0.20, 0.08, 0.08 and 0.20 m. Model calorically perfect air with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.7. Use a 320 m/s, 300 K inlet and a static outlet pressure of 90000 Pa. Use no-slip nozzle walls.", "external_asset_ids": []}
{"task_id": "extended:nozzleCDV/10", "track": "extended", "case_id": "nozzleCDV/10", "family": "nozzleCDV", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a steady 2D compressible CDV nozzle turbulence comparison using foamRun -solver fluid with RAS kOmegaSST. Keep the supplied structured CDV mesh, thermophysical model, boundary conditions, endTime=0.005, deltaT=1e-6, and sampling fixed; this is the 2D RANS turbulence variant, replacing the physically unsuitable quasi-2D DDES design. Use a unit-length nozzle with axial stations at x=0, 0.4, 0.6 and 1.0 m and corresponding half-heights 0.20, 0.08, 0.08 and 0.20 m. Model calorically perfect air with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.7. Use a 320 m/s, 300 K inlet and a static outlet pressure of 90000 Pa. Use no-slip nozzle walls.", "external_asset_ids": []}
{"task_id": "extended:nozzleCDV/2", "track": "extended", "case_id": "nozzleCDV/2", "family": "nozzleCDV", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform the CDV baseline compressible nozzle case with foamRun -solver fluid, using the supplied structured CDV geometry and a throat-refined mesh. Change only the first converging-section cell count from 40 to 80 (with all solver, thermophysical, flow, boundary, and run settings unchanged); this is the mesh-resolution variant. Use a unit-length nozzle with axial stations at x=0, 0.4, 0.6 and 1.0 m and corresponding half-heights 0.20, 0.08, 0.08 and 0.20 m. Model calorically perfect air with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.7. Use a 320 m/s, 300 K inlet and a static outlet pressure of 90000 Pa. Use no-slip nozzle walls.", "external_asset_ids": []}
{"task_id": "extended:nozzleCDV/3", "track": "extended", "case_id": "nozzleCDV/3", "family": "nozzleCDV", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform the supplied CDV compressible nozzle case with foamRun -solver fluid at a reduced outlet back pressure of 95000 Pa. Keep the CDV geometry, mesh, solver, thermophysical model, inlet state, discretisation, and run controls fixed; this is the back-pressure variant distinct from the mesh-refined nozzleCDV/2 case. Use a unit-length nozzle with axial stations at x=0, 0.4, 0.6 and 1.0 m and corresponding half-heights 0.20, 0.08, 0.08 and 0.20 m. Model calorically perfect air with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.7. Use a 320 m/s, 300 K inlet and a static outlet pressure of 95000 Pa. Use no-slip nozzle walls.", "external_asset_ids": []}
{"task_id": "extended:nozzleCDV/4", "track": "extended", "case_id": "nozzleCDV/4", "family": "nozzleCDV", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible converging-diverging nozzle benchmark using OpenFOAM-13 with foamRun -solver fluid. Back-pressure scan for subsonic, transonic, and supersonic CDV response. Change only the outlet static pressure by running three otherwise identical subcases with pBack=101325, 90000, and 35000 Pa; keep inlet velocity, geometry, mesh, solver, turbulence model, and schemes fixed. Run each subcase from t=0 to t=0.005; deltaT=1e-6; write results every 0.001 simulation-time units. Use a unit-length nozzle with axial stations at x=0, 0.4, 0.6 and 1.0 m and corresponding half-heights 0.20, 0.08, 0.08 and 0.20 m. Model calorically perfect air with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.7. For every branch use a 300 K inlet and the 320 m/s baseline inlet speed; vary only the outlet pressure values stated above. Use no-slip nozzle walls.", "external_asset_ids": []}
{"task_id": "extended:nozzleCDV/5", "track": "extended", "case_id": "nozzleCDV/5", "family": "nozzleCDV", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible converging-diverging nozzle benchmark using OpenFOAM-13 with foamRun -solver fluid. Mesh-type variant for the design-table comparison between the structured blockMesh baseline and a non-structured/polyhedral mesh. Change only the mesh representation by starting from the same CDV blockMesh geometry and converting the hex mesh with polyDualMesh using featureAngle=70; keep the geometry envelope, solver, laminar model, target flow condition, boundary conditions, and numerical schemes otherwise fixed. Run transient PIMPLE-style iterations from t=0 to t=0.005; deltaT=1e-6; write results every 0.001 simulation-time units. Compare this case against nozzleCDV/1 as the structured-mesh reference. Use a unit-length nozzle with axial stations at x=0, 0.4, 0.6 and 1.0 m and corresponding half-heights 0.20, 0.08, 0.08 and 0.20 m. Model calorically perfect air with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.7. Use a 320 m/s, 300 K inlet and a static outlet pressure of 90000 Pa. Use no-slip nozzle walls.", "external_asset_ids": []}
{"task_id": "extended:nozzleCDV/6", "track": "extended", "case_id": "nozzleCDV/6", "family": "nozzleCDV", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible converging-diverging nozzle benchmark using OpenFOAM-13 with foamRun -solver fluid. Discretisation-format variant from the design table: run an upwind stabilisation stage first, then switch to the stable higher-order linear/limited convection treatment used by the baseline for the remaining time. Change only the convection discretisation by running with system/fvSchemes.upwind to t=0.0025 and then continuing from latestTime with system/fvSchemes.limitedLinear to t=0.005; keep geometry, mesh, solver, laminar model, flow target, and boundary conditions fixed. Write results every 0.001 simulation-time units. Use distinct upwind and limitedLinear log suffixes so the second stage is executed rather than skipped by RunFunctions. Use a unit-length nozzle with axial stations at x=0, 0.4, 0.6 and 1.0 m and corresponding half-heights 0.20, 0.08, 0.08 and 0.20 m. Model calorically perfect air with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.7. Use a 320 m/s, 300 K inlet and a static outlet pressure of 90000 Pa. Use no-slip nozzle walls.", "external_asset_ids": []}
{"task_id": "extended:nozzleCDV/7", "track": "extended", "case_id": "nozzleCDV/7", "family": "nozzleCDV", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible converging-diverging nozzle benchmark using OpenFOAM-13 with foamRun -solver fluid. Boundary-condition variant from the design table using total pressure and total temperature at the inlet with a static-pressure outlet. Change only the inlet/outlet boundary-condition formulation; keep the CDV geometry, structured 2D mesh, solver, laminar model, target flow condition, and numerical schemes fixed. Run transient PIMPLE-style iterations from t=0 to t=0.005; deltaT=1e-6; write results every 0.001 simulation-time units. Use a unit-length nozzle with axial stations at x=0, 0.4, 0.6 and 1.0 m and corresponding half-heights 0.20, 0.08, 0.08 and 0.20 m. Model calorically perfect air with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.7. Use inlet total pressure 350000 Pa and total temperature 300 K, with a 90000 Pa static-pressure outlet. Use no-slip nozzle walls.", "external_asset_ids": []}
{"task_id": "extended:nozzleCDV/8", "track": "extended", "case_id": "nozzleCDV/8", "family": "nozzleCDV", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible converging-diverging nozzle benchmark using OpenFOAM-13 with foamRun -solver shockFluid. Solver-comparison variant using shockFluid, the OpenFOAM-13 replacement for the legacy rhoCentralFoam central-upwind shock-capturing solver. Change only the solver family and its required convection schemes; keep geometry, mesh, target inlet speed, inlet thermodynamic state, wall treatment, and turbulence model fixed while using shockFluid-compatible outlet extrapolation. Keep the CDV geometry, structured 2D mesh, thermophysical model, laminar model, physical flow condition, and pressure-density convection format div(phi,(p|rho)) unchanged unless this variant explicitly changes that one main variable. Run as transient PIMPLE-style iterations from t=0 to t=0.005; deltaT=1e-7; write results every 0.001 simulation-time units using a fixed-step shockFluid configuration aligned with the tutorial-style solver setup. Use a unit-length nozzle with axial stations at x=0, 0.4, 0.6 and 1.0 m and corresponding half-heights 0.20, 0.08, 0.08 and 0.20 m. Model calorically perfect air with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.7. Use a 320 m/s, 300 K inlet and the 90000 Pa baseline pressure level, with shock-compatible extrapolation at the outlet. Use no-slip nozzle walls.", "external_asset_ids": []}
{"task_id": "extended:nozzleCDV/9", "track": "extended", "case_id": "nozzleCDV/9", "family": "nozzleCDV", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible converging-diverging nozzle benchmark using OpenFOAM-13 with foamRun -solver fluid. Dimension variant from the design table: use a true 2D axisymmetric CDV nozzle simplification represented by a small-angle wedge mesh, not a planar half-channel symmetry-plane approximation. Preserve the axial converging-diverging radius profile, collapse the centerline to an axis patch with empty field conditions, and use front/back wedge patches so the OpenFOAM wedge formulation includes the cylindrical-coordinate geometric effect. Use a standard compressible nozzle boundary-condition formulation with totalPressure p0=160000 Pa and totalTemperature T0=300 K at the inlet, pressureInletOutletVelocity for the open velocity boundaries, and a static-pressure outlet p=90000 Pa. Use slip walls for the inviscid/laminar axisymmetric nozzle-wall idealisation. Run transient PIMPLE pseudo-time integration to a quasi-steady converged state from t=0 to t=0.1 with fixed deltaT=1e-5, adjustTimeStep=no, maxCo=0.5, maxDeltaT=1e-5, and writeInterval=0.02. Use a unit-length nozzle with axial stations at x=0, 0.4, 0.6 and 1.0 m and corresponding half-heights 0.20, 0.08, 0.08 and 0.20 m. Model calorically perfect air with molecular weight 28.9, Cp=1005 J/(kg K), viscosity 1.8e-5 Pa s and Pr=0.7. Use the axisymmetric wedge interpretation and the total-pressure/total-temperature and back-pressure values already stated above.", "external_asset_ids": []}
{"task_id": "extended:riemann2D/1", "track": "extended", "case_id": "riemann2D/1", "family": "riemann2D", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Configure and run the CFD-China four-quadrant two-dimensional Riemann problem in OpenFOAM-13 using foamRun -solver shockFluid. Model an inviscid calorically perfect gas with gamma=1.4 using molWeight=11640.3, Cp=2.5, hf=0, mu=0 and Pr=1. Use the square domain [-5,5] x [-5,5] on a uniform 800 x 800 mesh with one cell through the empty direction. Initialize the primitive states (rho,p,u,v) as NE=(1.5,1.5,0,0), NW=(0.5323,0.3,1.206,0), SW=(0.138,0.029,1.206,1.206), and SE=(0.5323,0.3,0,1.206), and derive temperature from the perfect-gas equation of state. Use the Kurganov central-upwind flux, vanAlbada reconstruction for rho and T, and vanAlbadaV reconstruction for U. Use zero-gradient conditions on the four outer sides and empty front/back patches. Advance to t=1.5 with adaptive time stepping and maxCo=0.2, writing results every 0.15 time units. Provide time-resolved density and pressure contours together with final rho and p profiles along the horizontal and vertical centre-lines.", "external_asset_ids": []}
{"task_id": "extended:riemann2D/10", "track": "extended", "case_id": "riemann2D/10", "family": "riemann2D", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Evaluate restart fidelity for the CFD-China four-quadrant two-dimensional Riemann problem using OpenFOAM-13 with foamRun -solver shockFluid. Model an inviscid calorically perfect gas with gamma=1.4 using molWeight=11640.3, Cp=2.5, hf=0, mu=0 and Pr=1. Initialize the primitive states (rho,p,u,v) as NE=(1.5,1.5,0,0), NW=(0.5323,0.3,1.206,0), SW=(0.138,0.029,1.206,1.206), and SE=(0.5323,0.3,0,1.206), and derive temperature from the perfect-gas equation of state. Use a uniform 600 x 600 mesh over [-5,5] x [-5,5] with one cell through the empty direction, the Kurganov flux, vanAlbada/vanAlbadaV reconstruction, zero-gradient outer boundaries, adaptive stepping at maxCo=0.2 and a final time of 1.5 with outputs every 0.15. Run one branch continuously from t=0 to 1.5. Run a second branch from t=0 to 0.75, write a complete binary restart state, and continue from the latest saved time to t=1.5 without reinitializing the fields. Compare the final rho, p, T and U fields, both centre-line profiles, time-step histories and output-time alignment between the continuous and restarted runs.", "external_asset_ids": []}
{"task_id": "extended:riemann2D/2", "track": "extended", "case_id": "riemann2D/2", "family": "riemann2D", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a spatial-convergence study of the CFD-China four-quadrant two-dimensional Riemann problem using OpenFOAM-13 with foamRun -solver shockFluid. Model an inviscid calorically perfect gas with gamma=1.4 using molWeight=11640.3, Cp=2.5, hf=0, mu=0 and Pr=1. Use the square domain [-5,5] x [-5,5] with one cell through the empty direction. Initialize the primitive states (rho,p,u,v) as NE=(1.5,1.5,0,0), NW=(0.5323,0.3,1.206,0), SW=(0.138,0.029,1.206,1.206), and SE=(0.5323,0.3,0,1.206), and derive temperature from the perfect-gas equation of state. Use the Kurganov central-upwind flux, vanAlbada reconstruction for rho and T, and vanAlbadaV reconstruction for U. Use zero-gradient conditions on the four outer sides and empty front/back patches. Advance to t=1.5 with adaptive time stepping and maxCo=0.2, writing results every 0.15 time units. Run otherwise identical uniform 200 x 200, 400 x 400 and 800 x 800 meshes, with outputs at the same physical times. Compare the density and pressure fields and centre-line profiles across the three resolutions, and discuss the observed convergence behaviour in smooth regions and across shocks and contact discontinuities.", "external_asset_ids": []}
{"task_id": "extended:riemann2D/3", "track": "extended", "case_id": "riemann2D/3", "family": "riemann2D", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Assess Courant-number sensitivity for the CFD-China four-quadrant two-dimensional Riemann problem using OpenFOAM-13 with foamRun -solver shockFluid. Model an inviscid calorically perfect gas with gamma=1.4 using molWeight=11640.3, Cp=2.5, hf=0, mu=0 and Pr=1. Use a fixed uniform 600 x 600 mesh on [-5,5] x [-5,5] with one cell through the empty direction. Initialize the primitive states (rho,p,u,v) as NE=(1.5,1.5,0,0), NW=(0.5323,0.3,1.206,0), SW=(0.138,0.029,1.206,1.206), and SE=(0.5323,0.3,0,1.206), and derive temperature from the perfect-gas equation of state. Use the Kurganov flux with vanAlbada reconstruction for rho and T and vanAlbadaV for U, with zero-gradient outer boundaries. Run otherwise identical adaptive-time-step branches with maxCo=0.1 and maxCo=0.2 to t=1.5, writing both at the same physical times every 0.15. Compare their density and pressure fields, centre-line profiles, wave positions and computational effort.", "external_asset_ids": []}
{"task_id": "extended:riemann2D/4", "track": "extended", "case_id": "riemann2D/4", "family": "riemann2D", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Compare the Kurganov and Tadmor central fluxes for the CFD-China four-quadrant two-dimensional Riemann problem using OpenFOAM-13 with foamRun -solver shockFluid. Model an inviscid calorically perfect gas with gamma=1.4 using molWeight=11640.3, Cp=2.5, hf=0, mu=0 and Pr=1. Use a uniform 600 x 600 mesh on [-5,5] x [-5,5] with one cell through the empty direction. Initialize the primitive states (rho,p,u,v) as NE=(1.5,1.5,0,0), NW=(0.5323,0.3,1.206,0), SW=(0.138,0.029,1.206,1.206), and SE=(0.5323,0.3,0,1.206), and derive temperature from the perfect-gas equation of state. Use vanAlbada reconstruction for rho and T and vanAlbadaV for U, zero-gradient outer boundaries, adaptive stepping with maxCo=0.2, and run to t=1.5 with outputs every 0.15. Change only the flux formulation between the two branches, and compare their density and pressure fields, centre-line profiles, discontinuity resolution, numerical oscillations, robustness and computational cost.", "external_asset_ids": []}
{"task_id": "extended:riemann2D/5", "track": "extended", "case_id": "riemann2D/5", "family": "riemann2D", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Assess reconstruction-limiter sensitivity for the CFD-China four-quadrant two-dimensional Riemann problem using OpenFOAM-13 with foamRun -solver shockFluid. Model an inviscid calorically perfect gas with gamma=1.4 using molWeight=11640.3, Cp=2.5, hf=0, mu=0 and Pr=1. Use a uniform 600 x 600 mesh on [-5,5] x [-5,5] with one cell through the empty direction. Initialize the primitive states (rho,p,u,v) as NE=(1.5,1.5,0,0), NW=(0.5323,0.3,1.206,0), SW=(0.138,0.029,1.206,1.206), and SE=(0.5323,0.3,0,1.206), and derive temperature from the perfect-gas equation of state. Retain the Kurganov flux, zero-gradient outer boundaries, adaptive stepping with maxCo=0.2 and an end time of 1.5 with outputs every 0.15. Compare a vanAlbada/vanAlbadaV branch against a vanLeer/vanLeerV branch, changing only the reconstruction limiter. Compare density and pressure fields and centre-line profiles, with attention to discontinuity sharpness, post-shock oscillations and robustness.", "external_asset_ids": []}
{"task_id": "extended:riemann2D/6", "track": "extended", "case_id": "riemann2D/6", "family": "riemann2D", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Evaluate mesh-orientation bias for the CFD-China four-quadrant two-dimensional Riemann problem using OpenFOAM-13 with foamRun -solver shockFluid. Model an inviscid calorically perfect gas with gamma=1.4 using molWeight=11640.3, Cp=2.5, hf=0, mu=0 and Pr=1. Use a uniform 600 x 600 Cartesian mesh on [-5,5] x [-5,5] with one cell through the empty direction. Initialize the primitive states (rho,p,u,v) as NE=(1.5,1.5,0,0), NW=(0.5323,0.3,1.206,0), SW=(0.138,0.029,1.206,1.206), and SE=(0.5323,0.3,0,1.206), and derive temperature from the perfect-gas equation of state. Run a baseline branch and a second branch in which the initial discontinuity geometry is rotated by 45 degrees while the mesh remains fixed. Define x'=(x+y)/sqrt(2) and y'=(-x+y)/sqrt(2), assign the same four states according to the signs of x' and y', and rotate their velocity vectors consistently into the physical x-y frame. Use the Kurganov flux, vanAlbada/vanAlbadaV reconstruction, zero-gradient outer boundaries and maxCo=0.2, and run both branches to t=1.5 with outputs every 0.15. Rotate the second result back to the baseline frame and compare the density and pressure fields on the common interior [-3.5,3.5] x [-3.5,3.5].", "external_asset_ids": []}
{"task_id": "extended:riemann2D/7", "track": "extended", "case_id": "riemann2D/7", "family": "riemann2D", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Assess domain-size and outer-boundary sensitivity for the CFD-China four-quadrant two-dimensional Riemann problem using OpenFOAM-13 with foamRun -solver shockFluid. Model an inviscid calorically perfect gas with gamma=1.4 using molWeight=11640.3, Cp=2.5, hf=0, mu=0 and Pr=1. Initialize the primitive states (rho,p,u,v) as NE=(1.5,1.5,0,0), NW=(0.5323,0.3,1.206,0), SW=(0.138,0.029,1.206,1.206), and SE=(0.5323,0.3,0,1.206), and derive temperature from the perfect-gas equation of state. Use one cell through the empty direction in both domains. Use the Kurganov flux, vanAlbada/vanAlbadaV reconstruction, zero-gradient outer boundaries and maxCo=0.2. Run a small domain [-2.5,2.5] x [-2.5,2.5] on a 300 x 300 mesh and a large domain [-5,5] x [-5,5] on a 600 x 600 mesh, so that both use the same spatial resolution. Advance both to t=1.5 and write at matched times every 0.15. Compare their flow fields on the common interior [-2,2] x [-2,2] and identify when and how the smaller outer boundary begins to affect the solution.", "external_asset_ids": []}
{"task_id": "extended:riemann2D/8", "track": "extended", "case_id": "riemann2D/8", "family": "riemann2D", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Stress-test positivity and nonlinear robustness for a strengthened four-quadrant two-dimensional Riemann interaction using OpenFOAM-13 with foamRun -solver shockFluid. Model an inviscid calorically perfect gas with gamma=1.4 using molWeight=11640.3, Cp=2.5, hf=0, mu=0 and Pr=1. Use a uniform 600 x 600 mesh on [-5,5] x [-5,5] with one cell through the empty direction. Initialize (rho,p,u,v) as NE=(1.5,3.0,0,0), NW=(0.5323,0.3,1.206,0), SW=(0.069,0.0145,1.206,1.206), and SE=(0.5323,0.3,0,1.206), deriving temperature consistently from the equation of state. Use the Kurganov flux, vanAlbada reconstruction for rho and T, vanAlbadaV for U, zero-gradient outer boundaries and adaptive stepping with maxCo=0.2. Attempt to reach t=1.5 without clipping, flooring or changing the stated physics. If the calculation fails, retain the failing configuration and identify the first failure time and affected field.", "external_asset_ids": []}
{"task_id": "extended:riemann2D/9", "track": "extended", "case_id": "riemann2D/9", "family": "riemann2D", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Evaluate parallel-decomposition invariance and solver scaling for the CFD-China four-quadrant two-dimensional Riemann problem using OpenFOAM-13 with foamRun -solver shockFluid. Model an inviscid calorically perfect gas with gamma=1.4 using molWeight=11640.3, Cp=2.5, hf=0, mu=0 and Pr=1. Initialize the primitive states (rho,p,u,v) as NE=(1.5,1.5,0,0), NW=(0.5323,0.3,1.206,0), SW=(0.138,0.029,1.206,1.206), and SE=(0.5323,0.3,0,1.206), and derive temperature from the perfect-gas equation of state. Use a uniform 800 x 800 mesh over [-5,5] x [-5,5] with one cell through the empty direction, the Kurganov flux, vanAlbada/vanAlbadaV reconstruction, zero-gradient outer boundaries, maxCo=0.2 and an end time of 1.5 with outputs every 0.15. Execute matched serial, two-rank and four-rank runs, using scotch decomposition for the parallel branches. Compare the reconstructed final fields and centre-line profiles and report speedup and parallel efficiency. Measure elapsed time for the foamRun solver phase only, excluding mesh generation, initialization, decomposition, reconstruction, sampling and comparison.", "external_asset_ids": []}
{"task_id": "extended:risingBubble/1", "track": "extended", "case_id": "risingBubble/1", "family": "risingBubble", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a 2D rising-bubble VOF validation case using OpenFOAM-13 with foamRun -solver incompressibleVoF, corresponding to the legacy interFoam application. Use a rectangular domain discretized with 20x40 cells; initialize a circular gas bubble of radius 0.15 centered at (0.5, 0.8) in liquid. Set sigma=24.5, water density=1000 kg/m3, air density=100 kg/m3, and downward gravity=0.98 m/s2. Use the baseline vanLeer VOF alpha-advection scheme without the explicit interfaceCompression scheme variant. Run from t=0 to t=7; deltaT=1e-3; write results every 0.1 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.5, maxAlphaCo=0.9, maxDeltaT=0.9. Use a 1 m wide and 2 m high tank, initially at rest. Treat the side and bottom boundaries as slip walls and the top as an open pressure boundary. The flow is laminar; the water and air kinematic viscosities are 0.01 and 0.01 m2/s, respectively.", "external_asset_ids": []}
{"task_id": "extended:risingBubble/10", "track": "extended", "case_id": "risingBubble/10", "family": "risingBubble", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a 2D rising-bubble VOF validation case using OpenFOAM-13 with foamRun -solver incompressibleVoF, corresponding to the legacy interFoam application. Use a rectangular domain discretized with 20x40 cells; initialize a circular gas bubble of radius 0.15 centered at (0.5, 0.8) in liquid. Set sigma=6.125, water density=1000 kg/m3, air density=100 kg/m3, liquid kinematic viscosity nu=0.1, air kinematic viscosity nu=0.1, and downward gravity=0.98 m/s2. Use the baseline vanLeer VOF alpha-advection scheme without the explicit interfaceCompression scheme variant. This is a high-Eotvos-number and high-Morton-number sensitivity variant using lower surface tension and higher viscosity than the baseline, intended to explore a strongly deformed/skirt-bubble regime. Run from t=0 to t=7; deltaT=1e-3; write results every 0.1 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.5, maxAlphaCo=0.9, maxDeltaT=0.9. Use a 1 m wide and 2 m high tank, initially at rest. Treat the side and bottom boundaries as slip walls and the top as an open pressure boundary. The flow is laminar; the water and air kinematic viscosities are 0.1 and 0.1 m2/s, respectively.", "external_asset_ids": []}
{"task_id": "extended:risingBubble/2", "track": "extended", "case_id": "risingBubble/2", "family": "risingBubble", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a 2D rising-bubble VOF validation case using OpenFOAM-13 with foamRun -solver incompressibleVoF, corresponding to the legacy interFoam application. Use a rectangular domain discretized with 40x80 cells; initialize a circular gas bubble of radius 0.15 centered at (0.5, 0.8) in liquid. Set sigma=24.5, water density=1000 kg/m3, air density=100 kg/m3, and downward gravity=0.98 m/s2. Use the baseline vanLeer VOF alpha-advection scheme without the explicit interfaceCompression scheme variant. Run from t=0 to t=7; deltaT=1e-3; write results every 0.1 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.5, maxAlphaCo=0.9, maxDeltaT=0.9. Use a 1 m wide and 2 m high tank, initially at rest. Treat the side and bottom boundaries as slip walls and the top as an open pressure boundary. The flow is laminar; the water and air kinematic viscosities are 0.01 and 0.01 m2/s, respectively.", "external_asset_ids": []}
{"task_id": "extended:risingBubble/3", "track": "extended", "case_id": "risingBubble/3", "family": "risingBubble", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a 2D rising-bubble VOF validation case using OpenFOAM-13 with foamRun -solver incompressibleVoF, corresponding to the legacy interFoam application. Use a rectangular domain discretized with 80x160 cells; initialize a circular gas bubble of radius 0.15 centered at (0.5, 0.8) in liquid. Set sigma=24.5, water density=1000 kg/m3, air density=100 kg/m3, and downward gravity=0.98 m/s2. Use the baseline vanLeer VOF alpha-advection scheme without the explicit interfaceCompression scheme variant. Run from t=0 to t=7; deltaT=1e-3; write results every 0.1 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.5, maxAlphaCo=0.9, maxDeltaT=0.9. Use a 1 m wide and 2 m high tank, initially at rest. Treat the side and bottom boundaries as slip walls and the top as an open pressure boundary. The flow is laminar; the water and air kinematic viscosities are 0.01 and 0.01 m2/s, respectively.", "external_asset_ids": []}
{"task_id": "extended:risingBubble/4", "track": "extended", "case_id": "risingBubble/4", "family": "risingBubble", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a 2D rising-bubble VOF validation case using OpenFOAM-13 with foamRun -solver incompressibleVoF, corresponding to the legacy interFoam application. Use a rectangular domain discretized with 20x40 cells; initialize a circular gas bubble of radius 0.15 centered at (0.5, 0.8) in liquid. Set sigma=24.5, water density=1000 kg/m3, air density=100 kg/m3, and downward gravity=0.98 m/s2. Change only the interface-capturing scheme relative to the vanLeer baseline: use the explicit interfaceCompression alpha-transport scheme with a linear base interpolation instead of the baseline Gauss vanLeer alpha advection. Run from t=0 to t=7; deltaT=1e-3; write results every 0.1 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.5, maxAlphaCo=0.9, maxDeltaT=0.9. Use a 1 m wide and 2 m high tank, initially at rest. Treat the side and bottom boundaries as slip walls and the top as an open pressure boundary. The flow is laminar; the water and air kinematic viscosities are 0.01 and 0.01 m2/s, respectively.", "external_asset_ids": []}
{"task_id": "extended:risingBubble/5", "track": "extended", "case_id": "risingBubble/5", "family": "risingBubble", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a 2D rising-bubble VOF validation case using OpenFOAM-13 with foamRun -solver incompressibleVoF, corresponding to the legacy interFoam application. Use a rectangular domain discretized with 20x40 cells; initialize a circular gas bubble of radius 0.15 centered at (0.5, 0.8) in liquid. Set sigma=24.5, water density=1000 kg/m3, air density=100 kg/m3, and downward gravity=0.98 m/s2. This variant follows the PDF design intent of an isoAdvector geometric reconstruction comparison, but OpenFOAM Foundation v13 does not provide the original isoAdvector method in this solver path; implement the closest available geometric VOF analogue as Gauss PLIC interfaceCompression vanLeer 1. Therefore the research purpose is comparable to the isoAdvector variant, while the numerical method entity is the Foundation-v13 PLIC/interfaceCompression approximation rather than native isoAdvector. Run from t=0 to t=7; deltaT=1e-3; write results every 0.1 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.5, maxAlphaCo=0.9, maxDeltaT=0.9. Use a 1 m wide and 2 m high tank, initially at rest. Treat the side and bottom boundaries as slip walls and the top as an open pressure boundary. The flow is laminar; the water and air kinematic viscosities are 0.01 and 0.01 m2/s, respectively.", "external_asset_ids": []}
{"task_id": "extended:risingBubble/6", "track": "extended", "case_id": "risingBubble/6", "family": "risingBubble", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a 2D rising-bubble VOF validation case using OpenFOAM-13 with foamRun -solver incompressibleVoF, corresponding to the legacy interFoam application. Use a rectangular domain discretized with 20x40 cells; initialize a circular gas bubble of radius 0.15 centered at (0.5, 0.8) in liquid. Set sigma=12.25, water density=1000 kg/m3, air density=100 kg/m3, and downward gravity=0.98 m/s2. Use the baseline vanLeer VOF alpha-advection scheme without the explicit interfaceCompression scheme variant. Run from t=0 to t=7; deltaT=1e-3; write results every 0.1 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.5, maxAlphaCo=0.9, maxDeltaT=0.9. Use a 1 m wide and 2 m high tank, initially at rest. Treat the side and bottom boundaries as slip walls and the top as an open pressure boundary. The flow is laminar; the water and air kinematic viscosities are 0.01 and 0.01 m2/s, respectively.", "external_asset_ids": []}
{"task_id": "extended:risingBubble/7", "track": "extended", "case_id": "risingBubble/7", "family": "risingBubble", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a 2D rising-bubble VOF validation case using OpenFOAM-13 with foamRun -solver incompressibleVoF, corresponding to the legacy interFoam application. Use a rectangular domain discretized with 20x40 cells; initialize a circular gas bubble of radius 0.15 centered at (0.5, 0.8) in liquid. Set sigma=49.0, water density=1000 kg/m3, air density=100 kg/m3, and downward gravity=0.98 m/s2. Use the baseline vanLeer VOF alpha-advection scheme without the explicit interfaceCompression scheme variant. Run from t=0 to t=7; deltaT=1e-3; write results every 0.1 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.5, maxAlphaCo=0.9, maxDeltaT=0.9. Use a 1 m wide and 2 m high tank, initially at rest. Treat the side and bottom boundaries as slip walls and the top as an open pressure boundary. The flow is laminar; the water and air kinematic viscosities are 0.01 and 0.01 m2/s, respectively.", "external_asset_ids": []}
{"task_id": "extended:risingBubble/8", "track": "extended", "case_id": "risingBubble/8", "family": "risingBubble", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a 2D rising-bubble VOF validation case using OpenFOAM-13 with foamRun -solver incompressibleVoF, corresponding to the legacy interFoam application. Use a rectangular domain discretized with 20x40 cells; initialize a circular gas bubble of radius 0.15 centered at (0.5, 0.8) in liquid. Set sigma=24.5, water density=1000 kg/m3, air density=100 kg/m3, and downward gravity=0.98 m/s2. Use the baseline vanLeer VOF alpha-advection scheme without the explicit interfaceCompression scheme variant. Use adaptive mesh refinement with dynamicRefineFvMesh to refine the mesh around the gas-liquid interface during the calculation, while keeping the initial coarse mesh and baseline physical properties; implement the reference case as a thin quasi-2D slab with front/back symmetry planes if needed for OpenFOAM dynamic refinement. Run from t=0 to t=7; deltaT=1e-3; write results every 0.1 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.5, maxAlphaCo=0.9, maxDeltaT=0.9. Use a 1 m wide and 2 m high tank, initially at rest. Treat the side and bottom boundaries as slip walls and the top as an open pressure boundary. The flow is laminar; the water and air kinematic viscosities are 0.01 and 0.01 m2/s, respectively.", "external_asset_ids": []}
{"task_id": "extended:risingBubble/9", "track": "extended", "case_id": "risingBubble/9", "family": "risingBubble", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a 2D rising-bubble VOF validation case using OpenFOAM-13 with foamRun -solver incompressibleVoF, corresponding to the legacy interFoam application. Use a rectangular domain discretized with 20x40 cells; initialize a circular gas bubble of radius 0.15 centered at (0.5, 0.8) in liquid. Set sigma=6.125, water density=1000 kg/m3, air density=100 kg/m3, and downward gravity=0.98 m/s2. Use the baseline vanLeer VOF alpha-advection scheme without the explicit interfaceCompression scheme variant. This is the high-Eotvos-number variant, using the lower surface tension as a physically consistent high-Eo parameter set so the bubble deforms more strongly than the baseline rising-bubble case. Run from t=0 to t=7; deltaT=1e-3; write results every 0.1 using writeControl=adjustableRunTime. Use adjustTimeStep=yes, maxCo=0.5, maxAlphaCo=0.9, maxDeltaT=0.9. Use a 1 m wide and 2 m high tank, initially at rest. Treat the side and bottom boundaries as slip walls and the top as an open pressure boundary. The flow is laminar; the water and air kinematic viscosities are 0.01 and 0.01 m2/s, respectively.", "external_asset_ids": []}
{"task_id": "extended:supersonicCrossJet/1", "track": "extended", "case_id": "supersonicCrossJet/1", "family": "supersonicCrossJet", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible supersonic jet-in-crossflow benchmark using the legacy rhoSimpleFoam steady SIMPLE solver in OpenFOAM-13. Variant: baseline Ma=2.0 and reference pressure ratio. Keep the physical geometry and inlet states unchanged except for the variant named here. This is a non-smoke steady benchmark: run steady iterations with deltaT=1 to endTime=1000 and write every 250 iterations. Judge success by solver stability, residual/continuity history, and final-window field changes rather than by a single iteration. Use a quasi-2D channel extending from x=-3.33333 to 2 m with a height of 1 m. A 0.05 m wide jet slot lies in the lower wall immediately upstream of x=0; the remaining solid boundaries are slip walls and the right boundary is an extrapolating outlet. Set the main-stream state to U=(801.997 0 0) m/s, p=100000 Pa and T=400 K, and the jet state to U=(0 347.275 0) m/s, p=100000 Pa and T=300 K. Model laminar calorically perfect air with molecular weight 28.96, Cp=1004.5 J/(kg K), constant viscosity 1e-5 Pa s and Pr=1.", "external_asset_ids": []}
{"task_id": "extended:supersonicCrossJet/10", "track": "extended", "case_id": "supersonicCrossJet/10", "family": "supersonicCrossJet", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible supersonic jet-in-crossflow benchmark using the rhoPimpleFoam-style pseudo-transient solver switch in OpenFOAM-13 via foamRun -solver fluid. Variant: rhoPimpleFoam pseudo-transient solver-family switch relative to the rhoSimpleFoam steady baseline. Keep the Ma=2 physical geometry and inlet states of the baseline. Run a non-smoke transient PIMPLE window from t=0 to t=0.05 with deltaT=2e-6 and write every 0.005 simulation-time units. Use a quasi-2D channel extending from x=-3.33333 to 2 m with a height of 1 m. A 0.05 m wide jet slot lies in the lower wall immediately upstream of x=0; the remaining solid boundaries are slip walls and the right boundary is an extrapolating outlet. Set the main-stream state to U=(801.997 0 0) m/s, p=100000 Pa and T=400 K, and the jet state to U=(0 347.275 0) m/s, p=100000 Pa and T=300 K. Model laminar calorically perfect air with molecular weight 28.96, Cp=1004.5 J/(kg K), constant viscosity 1e-5 Pa s and Pr=1.", "external_asset_ids": []}
{"task_id": "extended:supersonicCrossJet/2", "track": "extended", "case_id": "supersonicCrossJet/2", "family": "supersonicCrossJet", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible supersonic jet-in-crossflow benchmark using the legacy rhoSimpleFoam steady SIMPLE solver in OpenFOAM-13. Variant: mainflow Mach number Ma=3.0. Keep the physical geometry and inlet states unchanged except for the variant named here. This is a non-smoke steady benchmark: run steady iterations with deltaT=1 to endTime=1000 and write every 250 iterations. Judge success by solver stability, residual/continuity history, and final-window field changes rather than by a single iteration. Use a quasi-2D channel extending from x=-3.33333 to 2 m with a height of 1 m. A 0.05 m wide jet slot lies in the lower wall immediately upstream of x=0; the remaining solid boundaries are slip walls and the right boundary is an extrapolating outlet. Set the main-stream state to U=(1203 0 0) m/s, p=100000 Pa and T=400 K, and the jet state to U=(0 347.275 0) m/s, p=100000 Pa and T=300 K. Model laminar calorically perfect air with molecular weight 28.96, Cp=1004.5 J/(kg K), constant viscosity 1e-5 Pa s and Pr=1.", "external_asset_ids": []}
{"task_id": "extended:supersonicCrossJet/3", "track": "extended", "case_id": "supersonicCrossJet/3", "family": "supersonicCrossJet", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible supersonic jet-in-crossflow benchmark using the legacy rhoSimpleFoam steady SIMPLE solver in OpenFOAM-13. Variant: low jet-to-mainstream pressure ratio. Keep the physical geometry and inlet states unchanged except for the variant named here. This is a non-smoke steady benchmark: run steady iterations with deltaT=1 to endTime=1000 and write every 250 iterations. Judge success by solver stability, residual/continuity history, and final-window field changes rather than by a single iteration. Use a quasi-2D channel extending from x=-3.33333 to 2 m with a height of 1 m. A 0.05 m wide jet slot lies in the lower wall immediately upstream of x=0; the remaining solid boundaries are slip walls and the right boundary is an extrapolating outlet. Set the main-stream state to U=(801.997 0 0) m/s, p=100000 Pa and T=400 K, and the jet state to U=(0 347.275 0) m/s, p=50000 Pa and T=300 K. Model laminar calorically perfect air with molecular weight 28.96, Cp=1004.5 J/(kg K), constant viscosity 1e-5 Pa s and Pr=1.", "external_asset_ids": []}
{"task_id": "extended:supersonicCrossJet/4", "track": "extended", "case_id": "supersonicCrossJet/4", "family": "supersonicCrossJet", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible supersonic jet-in-crossflow benchmark using the legacy rhoSimpleFoam steady SIMPLE solver in OpenFOAM-13. Variant: high jet-to-mainstream pressure ratio. Keep the physical geometry and inlet states unchanged except for the variant named here. This is a non-smoke steady benchmark: run steady iterations with deltaT=1 to endTime=1000 and write every 250 iterations. Judge success by solver stability, residual/continuity history, and final-window field changes rather than by a single iteration. Use a quasi-2D channel extending from x=-3.33333 to 2 m with a height of 1 m. A 0.05 m wide jet slot lies in the lower wall immediately upstream of x=0; the remaining solid boundaries are slip walls and the right boundary is an extrapolating outlet. Set the main-stream state to U=(801.997 0 0) m/s, p=100000 Pa and T=400 K, and the jet state to U=(0 347.275 0) m/s, p=200000 Pa and T=300 K. Model laminar calorically perfect air with molecular weight 28.96, Cp=1004.5 J/(kg K), constant viscosity 1e-5 Pa s and Pr=1.", "external_asset_ids": []}
{"task_id": "extended:supersonicCrossJet/5", "track": "extended", "case_id": "supersonicCrossJet/5", "family": "supersonicCrossJet", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible supersonic jet-in-crossflow benchmark using the legacy rhoSimpleFoam steady SIMPLE solver in OpenFOAM-13. Variant: 30 degree injection angle. Keep the physical geometry and inlet states unchanged except for the variant named here. This is a non-smoke steady benchmark: run steady iterations with deltaT=1 to endTime=1000 and write every 250 iterations. Judge success by solver stability, residual/continuity history, and final-window field changes rather than by a single iteration. Use a quasi-2D channel extending from x=-3.33333 to 2 m with a height of 1 m. A 0.05 m wide jet slot lies in the lower wall immediately upstream of x=0; the remaining solid boundaries are slip walls and the right boundary is an extrapolating outlet. Set the main-stream state to U=(801.997 0 0) m/s, p=100000 Pa and T=400 K, and the jet state to U=(300.749 173.637 0) m/s, p=100000 Pa and T=300 K. Model laminar calorically perfect air with molecular weight 28.96, Cp=1004.5 J/(kg K), constant viscosity 1e-5 Pa s and Pr=1.", "external_asset_ids": []}
{"task_id": "extended:supersonicCrossJet/6", "track": "extended", "case_id": "supersonicCrossJet/6", "family": "supersonicCrossJet", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible supersonic jet-in-crossflow benchmark using the legacy rhoSimpleFoam steady SIMPLE solver in OpenFOAM-13. Variant: 60 degree injection angle. Keep the physical geometry and inlet states unchanged except for the variant named here. This is a non-smoke steady benchmark: run steady iterations with deltaT=1 to endTime=1000 and write every 250 iterations. Judge success by solver stability, residual/continuity history, and final-window field changes rather than by a single iteration. Use a quasi-2D channel extending from x=-3.33333 to 2 m with a height of 1 m. A 0.05 m wide jet slot lies in the lower wall immediately upstream of x=0; the remaining solid boundaries are slip walls and the right boundary is an extrapolating outlet. Set the main-stream state to U=(801.997 0 0) m/s, p=100000 Pa and T=400 K, and the jet state to U=(173.637 300.749 0) m/s, p=100000 Pa and T=300 K. Model laminar calorically perfect air with molecular weight 28.96, Cp=1004.5 J/(kg K), constant viscosity 1e-5 Pa s and Pr=1.", "external_asset_ids": []}
{"task_id": "extended:supersonicCrossJet/7", "track": "extended", "case_id": "supersonicCrossJet/7", "family": "supersonicCrossJet", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform the compressible supersonic jet-in-crossflow benchmark with the same Ma=2, pressure ratio, thermophysical model, solver, and controls as the baseline, but refine the first active mainflow block in the streamwise direction from 40 to 80 cells. Preserve all other blocks, boundaries, and numerical schemes. This is the mesh-resolution variant; the 90-degree injection angle is already represented by the baseline case. Use a quasi-2D channel extending from x=-3.33333 to 2 m with a height of 1 m. A 0.05 m wide jet slot lies in the lower wall immediately upstream of x=0; the remaining solid boundaries are slip walls and the right boundary is an extrapolating outlet. Set the main-stream state to U=(801.997 0 0) m/s, p=100000 Pa and T=400 K, and the jet state to U=(0 347.275 0) m/s, p=100000 Pa and T=300 K. Model laminar calorically perfect air with molecular weight 28.96, Cp=1004.5 J/(kg K), constant viscosity 1e-5 Pa s and Pr=1.", "external_asset_ids": []}
{"task_id": "extended:supersonicCrossJet/8", "track": "extended", "case_id": "supersonicCrossJet/8", "family": "supersonicCrossJet", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible supersonic jet-in-crossflow benchmark using the legacy rhoSimpleFoam steady SIMPLE solver in OpenFOAM-13. Variant: unbounded Gauss upwind convection retained for the full steady run, distinct from the bounded-upwind baseline. Keep the physical geometry and inlet states unchanged except for the variant named here. This is a non-smoke steady benchmark: run steady iterations with deltaT=1 to endTime=1000 and write every 250 iterations. Judge success by solver stability, residual/continuity history, and final-window field changes rather than by a single iteration. Use a quasi-2D channel extending from x=-3.33333 to 2 m with a height of 1 m. A 0.05 m wide jet slot lies in the lower wall immediately upstream of x=0; the remaining solid boundaries are slip walls and the right boundary is an extrapolating outlet. Set the main-stream state to U=(801.997 0 0) m/s, p=100000 Pa and T=400 K, and the jet state to U=(0 347.275 0) m/s, p=100000 Pa and T=300 K. Model laminar calorically perfect air with molecular weight 28.96, Cp=1004.5 J/(kg K), constant viscosity 1e-5 Pa s and Pr=1.", "external_asset_ids": []}
{"task_id": "extended:supersonicCrossJet/9", "track": "extended", "case_id": "supersonicCrossJet/9", "family": "supersonicCrossJet", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a compressible supersonic jet-in-crossflow benchmark using the legacy rhoSimpleFoam steady SIMPLE solver in OpenFOAM-13. Variant: earlier transition from upwind to bounded limitedLinear 0.05 steady schemes. Keep the physical geometry and inlet states unchanged except for the variant named here. This is a non-smoke steady benchmark: run steady iterations with deltaT=1 to endTime=1000 and write every 250 iterations. Judge success by solver stability, residual/continuity history, and final-window field changes rather than by a single iteration. For this staged scheme variant, run system/fvSchemes.upwind from iteration 0 to 300, then continue from latestTime with system/fvSchemes.limitedLinear, using bounded limitedLinear 0.05 convection, to iteration 1000. Use a quasi-2D channel extending from x=-3.33333 to 2 m with a height of 1 m. A 0.05 m wide jet slot lies in the lower wall immediately upstream of x=0; the remaining solid boundaries are slip walls and the right boundary is an extrapolating outlet. Set the main-stream state to U=(801.997 0 0) m/s, p=100000 Pa and T=400 K, and the jet state to U=(0 347.275 0) m/s, p=100000 Pa and T=300 K. Model laminar calorically perfect air with molecular weight 28.96, Cp=1004.5 J/(kg K), constant viscosity 1e-5 Pa s and Pr=1.", "external_asset_ids": []}
{"task_id": "extended:yPlusVerification/1", "track": "extended", "case_id": "yPlusVerification/1", "family": "yPlusVerification", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a wall y+ verification in a 1D periodic turbulent channel using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to the legacy simpleFoam application with steady-state SIMPLE pressure-velocity coupling. Use cyclic streamwise boundaries, a no-slip wall, a symmetry-plane centreline, and an empty front/back direction. Use 15 wall-normal cells with a grading ratio of 1 and the RAS kOmega turbulence model. Use kinematic viscosity nu=2e-5 and drive the flow with meanVelocityForce Ubar=(0.4 0 0) on the fluid cellZone. Run steady-state SIMPLE iterations using startTime=0, endTime=500, deltaT=0.25, writeControl=runTime, and writeInterval=20 as the iteration and output controls. Compare the sampled u+ versus y+ wall-law profile against the Spalding law analytical profile. Take the half-channel height as 1 m.", "external_asset_ids": []}
{"task_id": "extended:yPlusVerification/10", "track": "extended", "case_id": "yPlusVerification/10", "family": "yPlusVerification", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a wall y+ verification viscosity-sensitivity comparison in a periodic half-channel using OpenFOAM-13 with foamRun -solver incompressibleFluid, steady SIMPLE coupling, a 30-cell wall-normal mesh with grading ratio 50, and RAS kEpsilon. Run three nominal branches labelled Re_tau_180, Re_tau_395, and Re_tau_590 using nu=0.005555555556, 0.002531645570, and 0.001694915254 respectively while keeping meanVelocityForce Ubar=(0.4 0 0), geometry, boundaries, and controls fixed. The labels identify the viscosity values obtained from an initial u_tau=1 estimate; do not assume they are achieved Reynolds numbers. For every converged branch, obtain u_tau from positive computed wall shear, calculate and report achieved Re_tau=u_tau*delta/nu with delta=1, and compare sampled u+ versus y+ against Spalding law. Fail post-processing if wall shear is unavailable. The half-channel height is 1 m; the nominal Reynolds-number labels are only branch names, and the achieved friction Reynolds number must come from the computed wall shear.", "external_asset_ids": []}
{"task_id": "extended:yPlusVerification/2", "track": "extended", "case_id": "yPlusVerification/2", "family": "yPlusVerification", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a wall y+ verification in a 1D periodic turbulent channel using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to the legacy simpleFoam application with steady-state SIMPLE pressure-velocity coupling. Use cyclic streamwise boundaries, a no-slip wall, a symmetry-plane centreline, and an empty front/back direction. Use 15 wall-normal cells with a grading ratio of 1 and the RAS kEpsilon turbulence model. Use kinematic viscosity nu=2e-5 and drive the flow with meanVelocityForce Ubar=(0.4 0 0) on the fluid cellZone. Run steady-state SIMPLE iterations using startTime=0, endTime=500, deltaT=0.25, writeControl=runTime, and writeInterval=20 as the iteration and output controls. Compare the sampled u+ versus y+ wall-law profile against the Spalding law analytical profile. Take the half-channel height as 1 m.", "external_asset_ids": []}
{"task_id": "extended:yPlusVerification/3", "track": "extended", "case_id": "yPlusVerification/3", "family": "yPlusVerification", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a wall y+ verification in a 1D periodic turbulent channel using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to the legacy simpleFoam application with steady-state SIMPLE pressure-velocity coupling. Use cyclic streamwise boundaries, a no-slip wall, a symmetry-plane centreline, and an empty front/back direction. Use 50 wall-normal cells with a grading ratio of 100 and the RAS LaunderSharmaKE low-Reynolds-number turbulence model. Use kinematic viscosity nu=2e-5 and drive the flow with meanVelocityForce Ubar=(0.4 0 0) on the fluid cellZone. Run steady-state SIMPLE iterations using startTime=0, endTime=2500, deltaT=0.25, writeControl=runTime, and writeInterval=100 as the iteration and output controls. Compare the sampled u+ versus y+ wall-law profile against the Spalding law analytical profile. Take the half-channel height as 1 m.", "external_asset_ids": []}
{"task_id": "extended:yPlusVerification/4", "track": "extended", "case_id": "yPlusVerification/4", "family": "yPlusVerification", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a wall y+ verification in a 1D periodic turbulent channel using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to the legacy simpleFoam application with steady-state SIMPLE pressure-velocity coupling. Use cyclic streamwise boundaries, a no-slip wall, a symmetry-plane centreline, and an empty front/back direction. Use 50 wall-normal cells with a grading ratio of 100 and the RAS LamBremhorstKE low-Reynolds-number turbulence model. Use kinematic viscosity nu=2e-5 and drive the flow with meanVelocityForce Ubar=(0.4 0 0) on the fluid cellZone. Run steady-state SIMPLE iterations using startTime=0, endTime=2500, deltaT=0.25, writeControl=runTime, and writeInterval=100 as the iteration and output controls. Compare the sampled u+ versus y+ wall-law profile against the Spalding law analytical profile. Take the half-channel height as 1 m.", "external_asset_ids": []}
{"task_id": "extended:yPlusVerification/5", "track": "extended", "case_id": "yPlusVerification/5", "family": "yPlusVerification", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a wall y+ verification in a 1D periodic turbulent channel using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to the legacy simpleFoam application with steady-state SIMPLE pressure-velocity coupling. Use cyclic streamwise boundaries, a no-slip wall, a symmetry-plane centreline, and an empty front/back direction. Use 50 wall-normal cells with a grading ratio of 100 and the RAS LienCubicKE low-Reynolds-number turbulence model. Use kinematic viscosity nu=2e-5 and drive the flow with meanVelocityForce Ubar=(0.4 0 0) on the fluid cellZone. Run steady-state SIMPLE iterations using startTime=0, endTime=2500, deltaT=0.25, writeControl=runTime, and writeInterval=100 as the iteration and output controls. Compare the sampled u+ versus y+ wall-law profile against the Spalding law analytical profile. Take the half-channel height as 1 m.", "external_asset_ids": []}
{"task_id": "extended:yPlusVerification/6", "track": "extended", "case_id": "yPlusVerification/6", "family": "yPlusVerification", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a wall y+ verification in a 1D periodic turbulent channel using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to the legacy simpleFoam application with steady-state SIMPLE pressure-velocity coupling. Use cyclic streamwise boundaries, a no-slip wall, a symmetry-plane centreline, and an empty front/back direction. Use 50 wall-normal cells with a grading ratio of 100 and the RAS v2f low-Reynolds-number turbulence model. Use kinematic viscosity nu=2e-5 and drive the flow with meanVelocityForce Ubar=(0.4 0 0) on the fluid cellZone. Run steady-state SIMPLE iterations using startTime=0, endTime=2500, deltaT=0.25, writeControl=runTime, and writeInterval=100 as the iteration and output controls. Compare the sampled u+ versus y+ wall-law profile against the Spalding law analytical profile. Take the half-channel height as 1 m.", "external_asset_ids": []}
{"task_id": "extended:yPlusVerification/7", "track": "extended", "case_id": "yPlusVerification/7", "family": "yPlusVerification", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a wall y+ verification in a 1D periodic turbulent channel using OpenFOAM-13 with foamRun -solver incompressibleFluid, corresponding to the legacy simpleFoam application with steady-state SIMPLE pressure-velocity coupling. Use cyclic streamwise boundaries, a no-slip wall, a symmetry-plane centreline, and an empty front/back direction. Use 50 wall-normal cells with a grading ratio of 100 and the RAS qZeta low-Reynolds-number turbulence model. Use kinematic viscosity nu=2e-5 and drive the flow with meanVelocityForce Ubar=(0.4 0 0) on the fluid cellZone. Run steady-state SIMPLE iterations using startTime=0, endTime=2500, deltaT=0.25, writeControl=runTime, and writeInterval=100 as the iteration and output controls. Compare the sampled u+ versus y+ wall-law profile against the Spalding law analytical profile. Take the half-channel height as 1 m.", "external_asset_ids": []}
{"task_id": "extended:yPlusVerification/8", "track": "extended", "case_id": "yPlusVerification/8", "family": "yPlusVerification", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform a steady wall y+ verification in the same 1D periodic channel as yPlusVerification/1 and /2, using foamRun -solver incompressibleFluid, SIMPLE coupling, RAS kOmegaSST, 15 wall-normal cells, uniform grading, nu=2e-5, meanVelocityForce Ubar=(0.4 0 0), endTime=500, deltaT=0.25, writeControl=runTime, and writeInterval=20. This is the third-model comparison against the kOmega and kEpsilon variants. Take the half-channel height as 1 m.", "external_asset_ids": []}
{"task_id": "extended:yPlusVerification/9", "track": "extended", "case_id": "yPlusVerification/9", "family": "yPlusVerification", "task_origin": "ExtFoamBench (EasyFoam authors)", "usr_requirement": "Perform the coarse-wall-resolution y+ verification variant with the standard RAS kOmega model on the 30-cell wall-normal mesh with simpleGrading ratio 50. Keep the periodic channel forcing, endTime=500, deltaT=0.25, sampling, and Spalding comparison workflow fixed; this is distinct from the 15-cell kOmega baseline because the mesh and resulting wall-resolution target differ. Take the half-channel height as 1 m. Use kinematic viscosity 2e-5 m2/s and target mean velocity 0.4 m/s.", "external_asset_ids": []}