Datasets:

rblrbl
/

plm-orchestrator-evals

Error code:   DatasetGenerationError
Exception:    CastError
Message:      Couldn't cast
id: string
domain: string
level: string
task: string
bbox: list<item: double>
  child 0, item: double
volume: double
rel_tol: double
reference: string
topic: string
question: string
answer: double
solution: string
unit: string
to
{'id': Value('string'), 'domain': Value('string'), 'level': Value('string'), 'topic': Value('string'), 'question': Value('string'), 'answer': Value('float64'), 'unit': Value('string'), 'rel_tol': Value('float64'), 'solution': Value('string')}
because column names don't match
Traceback:    Traceback (most recent call last):
                File "/usr/local/lib/python3.14/site-packages/datasets/builder.py", line 1835, in _prepare_split_single
                  for key, table in generator:
                                    ^^^^^^^^^
                File "/src/services/worker/src/worker/job_runners/config/parquet_and_info.py", line 621, in wrapped
                  for item in generator(*args, **kwargs):
                              ~~~~~~~~~^^^^^^^^^^^^^^^^^
                File "/usr/local/lib/python3.14/site-packages/datasets/packaged_modules/json/json.py", line 361, in _generate_tables
                  self._cast_table(pa_table, json_field_paths=json_field_paths),
                  ~~~~~~~~~~~~~~~~^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^
                File "/usr/local/lib/python3.14/site-packages/datasets/packaged_modules/json/json.py", line 132, in _cast_table
                  pa_table = table_cast(pa_table, self.info.features.arrow_schema)
                File "/usr/local/lib/python3.14/site-packages/datasets/table.py", line 2381, in table_cast
                  return cast_table_to_schema(table, schema)
                File "/usr/local/lib/python3.14/site-packages/datasets/table.py", line 2309, in cast_table_to_schema
                  raise CastError(
                  ...<3 lines>...
                  )
              datasets.table.CastError: Couldn't cast
              id: string
              domain: string
              level: string
              task: string
              bbox: list<item: double>
                child 0, item: double
              volume: double
              rel_tol: double
              reference: string
              topic: string
              question: string
              answer: double
              solution: string
              unit: string
              to
              {'id': Value('string'), 'domain': Value('string'), 'level': Value('string'), 'topic': Value('string'), 'question': Value('string'), 'answer': Value('float64'), 'unit': Value('string'), 'rel_tol': Value('float64'), 'solution': Value('string')}
              because column names don't match
              
              The above exception was the direct cause of the following exception:
              
              Traceback (most recent call last):
                File "/src/services/worker/src/worker/job_runners/config/parquet_and_info.py", line 1379, in compute_config_parquet_and_info_response
                  parquet_operations, partial, estimated_dataset_info = stream_convert_to_parquet(
                                                                        ~~~~~~~~~~~~~~~~~~~~~~~~~^
                      builder, max_dataset_size_bytes=max_dataset_size_bytes
                      ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^
                  )
                  ^
                File "/src/services/worker/src/worker/job_runners/config/parquet_and_info.py", line 956, in stream_convert_to_parquet
                  builder._prepare_split(split_generator=splits_generators[split], file_format="parquet")
                  ~~~~~~~~~~~~~~~~~~~~~~^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^
                File "/usr/local/lib/python3.14/site-packages/datasets/builder.py", line 1702, in _prepare_split
                  for job_id, done, content in self._prepare_split_single(
                                               ~~~~~~~~~~~~~~~~~~~~~~~~~~^
                      gen_kwargs=gen_kwargs, job_id=job_id, **_prepare_split_args
                      ^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^^
                  ):
                  ^
                File "/usr/local/lib/python3.14/site-packages/datasets/builder.py", line 1887, in _prepare_split_single
                  raise DatasetGenerationError("An error occurred while generating the dataset") from e
              datasets.exceptions.DatasetGenerationError: An error occurred while generating the dataset

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id string	domain string	level string	topic string	question string	answer float64	unit string	rel_tol float64	solution string
ae-f01	aerospace	intensive	orbits	A spacecraft makes a Hohmann transfer from a circular orbit 400 km above Earth to a circular orbit 20200 km above Earth. How long does the transfer take, in hours? Use GM = 3.986e14 m³/s² and an Earth radius of 6371 km.	2.975235	h	0.01	a = (r1 + r2)/2, t = pi sqrt(a^3/GM) (half the transfer period)
ae-f02	aerospace	intensive	orbits	An elliptical orbit has a perigee altitude of 500 km and an apogee altitude of 2000 km. What is the speed at apogee, in kilometers per second? Use GM = 3.986e14 m³/s² and an Earth radius of 6371 km.	6.552152	km/s	0.01	a = (rp + ra)/2, va = sqrt(GM (2/ra - 1/a))
ae-f03	aerospace	intensive	orbits	A satellite in a circular orbit 800 km above Earth fires its engine retrograde once to lower its perigee to 200 km above Earth. What delta-v does that burn take, in meters per second? Use GM = 3.986e14 m³/s² and an Earth radius of 6371 km.	164.577389	m/s	0.01	v_circ at r = R + 800 km minus apogee speed of the 200 x 800 km ellipse
ae-f04	aerospace	intensive	propulsion	A rocket launched straight up has an initial mass of 50 t and burns 35 t of propellant at 250 kg/s with a specific impulse of 300 s. Taking g0 = 9.80665 m/s², including gravity losses at a constant 9.81 m/s² and ignoring drag, what is its speed at burnout, in meters per second?	2,168.68197	m/s	0.01	ve = Isp g0, t = 35000/250 = 140 s, v = ve ln(m0/mf) - g t
ae-f05	aerospace	intensive	propulsion	A jet engine takes in 80 kg/s of air and exhausts it at 600 m/s while the aircraft flies at 250 m/s. Ignoring the fuel's mass flow, what thrust power does the engine deliver, in megawatts?	7	MW	0.01	F = mdot (ve - v), P = F v
ae-f06	aerospace	intensive	aerodynamics	An aircraft flies at 650 m/s where the air temperature is 223 K. With a ratio of specific heats of 1.4 and R = 287 J/(kg·K), what is the stagnation temperature, in kelvin?	433.303634	K	0.01	a = sqrt(g R T), M = v / a, T0 = T (1 + (g-1)/2 M^2)
ae-f07	aerospace	intensive	aerodynamics	An airliner flies at Mach 0.8 where the air temperature is 230 K and the density is 0.41 kg/m³. With a ratio of specific heats of 1.4 and R = 287 J/(kg·K), what is the dynamic pressure, in kilopascals?	12.124717	kPa	0.01	a = sqrt(g R T), v = M a, q = rho v^2 / 2
ae-f08	aerospace	intensive	flight-mechanics	An aircraft weighing 70 kN has a wing area of 30 square meters and a maximum lift coefficient of 1.6. What is its stall speed in a level turn at a bank angle of 45 degrees, where the air density is 1.225 kg/m³, in meters per second?	58.027366	m/s	0.01	n = 1/cos(bank), V = sqrt(2 n W / (rho S CLmax))
ae-f09	aerospace	intensive	flight-mechanics	An aircraft makes a level turn at 120 m/s with a bank angle of 30 degrees. Taking g = 9.81 m/s², how long does a full 360-degree turn take, in seconds?	133.122889	s	0.01	r = v^2 / (g tan(bank)), t = 2 pi r / v
ae-f10	aerospace	intensive	flight-mechanics	An aircraft weighing 50 kN with a wing area of 25 square meters flies at 80 m/s where the air density is 1.0 kg/m³. Its drag polar is CD = 0.025 + 0.05 CL² and its engines give 8 kN of thrust. What is its rate of climb, in meters per second?	7.1	m/s	0.01	q = rho v^2/2, CL = W/(q S), D = q S CD, RC = (T - D) v / W
ae-f11	aerospace	intensive	propulsion	A rocket nozzle expands gas from a chamber temperature of 3200 K to an exit pressure that is 2% of the chamber pressure. The gas has a ratio of specific heats of 1.25 and R = 330 J/(kg·K). Taking g0 = 9.80665 m/s² and ignoring pressure thrust, what is the specific impulse, in seconds?	244.112025	s	0.01	ve = sqrt(2g/(g-1) R T0 (1 - (pe/p0)^((g-1)/g))), Isp = ve / g0
ae-f12	aerospace	intensive	propulsion	A turbine takes 40 kg/s of gas at 1400 K and expands it through a pressure ratio of 4 with an isentropic efficiency of 90%. With a ratio of specific heats of 1.33 and cp = 1150 J/(kg·K), what power does it deliver, in megawatts?	16.869155	MW	0.01	T2s = T1 (1/r)^((g-1)/g), dT = eta (T1 - T2s), P = mdot cp dT
ae-f13	aerospace	intensive	orbits	A satellite is on an elliptical orbit with a perigee altitude of 400 km and an apogee altitude of 3000 km. How fast is it moving when it is 1000 km above Earth, in kilometers per second? Use GM = 3.986e14 m³/s² and an Earth radius of 6371 km.	7.665956	km/s	0.01	a = (rp + ra)/2, v = sqrt(GM (2/r - 1/a)) at r = R + 1000 km
ae-f14	aerospace	intensive	propulsion	A single-stage rocket carries 30000 kg of propellant and has a dry mass of 3000 kg not counting its payload. Its engine has a specific impulse of 350 s. Taking g0 = 9.80665 m/s², what is the largest payload it can give 5000 m/s of ideal delta-v, in kilograms?	6,113.183923	kg	0.01	R = exp(dv / (Isp g0)); (3000 + P + 30000) / (3000 + P) = R, so P = 30000/(R - 1) - 3000
ae-f15	aerospace	intensive	aerodynamics	A pitot-static tube on an aircraft in low-speed flight reads 3.2 kPa between total and static pressure, where the air density is 1.0 kg/m³. Treating the flow as incompressible, how long does the aircraft take to fly 50 km at that speed, in minutes?	10.416667	min	0.01	v = sqrt(2 dp / rho), t = d / v
ae-l-c01	aerospace	calm	aerodynamics	An aircraft flies at 680 m/s where the speed of sound is 340 m/s. What is its Mach number (unitless)?	2		0.01	M = v / a
ae-l-c02	aerospace	calm	aerodynamics	Air with a density of 0.6 kg/m³ flows at 200 m/s. What is its dynamic pressure, in kilopascals?	12	kPa	0.01	q = rho v^2 / 2
ae-l-c03	aerospace	calm	propulsion	A rocket engine expels 80 kg/s of propellant at 2500 m/s. Ignoring pressure thrust, what is its thrust, in kilonewtons?	200	kN	0.01	F = mdot ve
ae-l-c04	aerospace	calm	propulsion	A rocket engine has a specific impulse of 320 s. Taking g0 = 9.80665 m/s², what is its exhaust velocity, in meters per second?	3,138.128	m/s	0.01	ve = Isp g0
ae-l-c05	aerospace	calm	flight-mechanics	An aircraft weighing 120000 N has a wing area of 60 square meters. What is its wing loading, in pascals?	2,000	Pa	0.01	W / S
ae-l-c06	aerospace	calm	units	An aircraft cruises at 300 knots, where 1 knot is 0.5144 m/s. What is its speed, in meters per second?	154.32	m/s	0.01	v = knots x 0.5144
ae-l-c07	aerospace	calm	aerodynamics	A wing produces 50 kN of lift and 4 kN of drag. What is its lift-to-drag ratio (unitless)?	12.5		0.01	L / D
ae-l-c08	aerospace	calm	flight-mechanics	An aircraft makes a level turn at a bank angle of 60 degrees. What is its load factor (unitless)?	2		0.01	n = 1 / cos(bank)
ae-l-c09	aerospace	calm	propulsion	A launch vehicle has 900 kN of thrust and weighs 600 kN. What is its thrust-to-weight ratio (unitless)?	1.5		0.01	T / W
ae-l-c10	aerospace	calm	atmosphere	What is the air density at sea level in the International Standard Atmosphere, in kilograms per cubic meter?	1.225	kg/m^3	0.01	ISA sea level
ae-l-c11	aerospace	calm	flight-mechanics	A glider covers 18 km horizontally while descending from an altitude of 1500 m in still air. What is its glide ratio (unitless)?	12		0.01	L/D = distance / height
ae-l-c12	aerospace	calm	orbits	A satellite is in a circular orbit of radius 7000 km. What is its orbital speed, in kilometers per second? Use GM = 3.986e14 m³/s².	7.546049	km/s	0.01	v = sqrt(GM / r)
ae-l-a01	aerospace	alert	aerodynamics	A wing of 16 square meters flies at 70 m/s in air of density 1.1 kg/m³ with a lift coefficient of 1.2. What lift does it produce, in kilonewtons?	51.744	kN	0.01	L = rho v^2 S CL / 2
ae-l-a02	aerospace	alert	aerodynamics	An airliner with a wing area of 120 square meters flies at 230 m/s where the air density is 0.4 kg/m³. With a drag coefficient of 0.03, what is its drag, in kilonewtons?	38.088	kN	0.01	D = rho v^2 S CD / 2
ae-l-a03	aerospace	alert	aerodynamics	What is the speed of sound in air at 250 K, with a ratio of specific heats of 1.4 and R = 287 J/(kg·K), in meters per second?	316.93848	m/s	0.01	a = sqrt(g R T)
ae-l-a04	aerospace	alert	propulsion	A rocket with a specific impulse of 300 s burns from an initial mass of 50 t to a final mass of 20 t. Taking g0 = 9.80665 m/s², what is its ideal delta-v, in meters per second?	2,695.722752	m/s	0.01	dv = Isp g0 ln(m0 / mf)
ae-l-a05	aerospace	alert	flight-mechanics	A light aircraft weighing 9000 N has a wing area of 14 square meters and a maximum lift coefficient of 1.5. What is its stall speed at sea level, where the air density is 1.225 kg/m³, in meters per second?	26.452003	m/s	0.01	V = sqrt(2 W / (rho S CLmax))
ae-l-a06	aerospace	alert	aerodynamics	A wing with a chord of 1.5 m flies at 50 m/s in air of density 1.225 kg/m³ and viscosity 1.8e-5 Pa·s. What is its Reynolds number (unitless)?	5,104,166.666667		0.01	Re = rho v c / mu
ae-l-a07	aerospace	alert	flight-mechanics	An aircraft makes a level turn at 100 m/s with a bank angle of 30 degrees. Taking g = 9.81 m/s², what is its turn radius, in meters?	1,765.597153	m	0.01	r = v^2 / (g tan(bank))
ae-l-a08	aerospace	alert	flight-mechanics	An aircraft has 20 kN of drag at 540 km/h. What power is needed to overcome drag, in megawatts?	3	MW	0.01	P = D v, v = 150 m/s
ae-l-a09	aerospace	alert	orbits	What is the escape velocity from 500 km above Earth's surface, in kilometers per second? Use GM = 3.986e14 m³/s² and an Earth radius of 6371 km.	10.771438	km/s	0.01	v = sqrt(2 GM / r), r = R + h
ae-l-a10	aerospace	alert	orbits	A satellite is in a circular orbit of radius 8000 km. What is its orbital period, in minutes? Use GM = 3.986e14 m³/s².	118.684759	min	0.01	T = 2 pi sqrt(r^3 / GM)
ae-l-a11	aerospace	alert	propulsion	A rocket engine expels 150 kg/s at 2800 m/s. Its nozzle exit area is 0.8 square meters, the exit pressure is 70 kPa and the ambient pressure is 40 kPa. What is its total thrust, in kilonewtons?	444	kN	0.01	F = mdot ve + (pe - pa) Ae
ae-l-a12	aerospace	alert	propulsion	An engine produces 500 kN of thrust with a specific impulse of 280 s. Taking g0 = 9.80665 m/s², what is its propellant mass flow, in kilograms per second?	182.092181	kg/s	0.01	mdot = F / (Isp g0)
ae-l-a13	aerospace	alert	flight-mechanics	An aircraft weighing 64 kN flies at 120 m/s with 30 kN of thrust and 22 kN of drag. What is its rate of climb, in meters per second?	15	m/s	0.01	RC = (T - D) v / W
ae-l-a14	aerospace	alert	atmosphere	In the standard atmosphere's troposphere the temperature is 288.15 K at sea level and falls by 6.5 K per kilometer. What is the temperature at an altitude of 8 km, in kelvin?	236.15	K	0.01	T = T0 - lapse h
ae-l-i01	aerospace	intensive	orbits	What total delta-v does a Hohmann transfer take from a circular orbit 400 km above Earth to a circular orbit 1000 km above Earth, in kilometers per second? Use GM = 3.986e14 m³/s² and an Earth radius of 6371 km.	0.318759	km/s	0.01	two burns on the transfer ellipse
ae-l-i02	aerospace	intensive	aerodynamics	An aircraft flies at 500 m/s where the air temperature is 230 K and the pressure is 30 kPa. With a ratio of specific heats of 1.4 and R = 287 J/(kg·K), what is the stagnation pressure, in kilopascals?	136.292972	kPa	0.01	a, M, p0 = p (1 + (g-1)/2 M^2)^(g/(g-1))
ae-l-i03	aerospace	intensive	propulsion	A two-stage rocket has a liftoff mass of 80 t. Stage 1 burns 50 t of propellant at a specific impulse of 270 s, then drops its 5 t of dry mass. Stage 2 then starts at 25 t and burns 18 t of propellant at a specific impulse of 330 s. Taking g0 = 9.80665 m/s², what is the total ideal delta-v, in meters per second?	6,716.599801	m/s	0.01	stage 1: 80 -> 30 t; stage 2: 25 -> 7 t
ae-l-i04	aerospace	intensive	flight-mechanics	A jet cruises at 230 m/s with a lift-to-drag ratio of 16 and a thrust-specific fuel consumption of 0.55 per hour. Its weight falls from 1.25 to 1.0 times its final weight during the cruise. Using the Breguet range equation, how far does it fly, in kilometers?	5,374.919578	km	0.01	R = (V / c)(L/D) ln(Wi / Wf), c in 1/s
ae-l-i05	aerospace	intensive	flight-mechanics	An aircraft weighing 400 kN with a wing area of 250 square meters flies level at 220 m/s where the air density is 0.5 kg/m³. Its drag polar is CD = 0.022 + 0.05 CL². What power is needed to overcome drag, in megawatts?	15.222818	MW	0.01	CL = W/(qS), CD, D = q S CD, P = D V
ae-l-i06	aerospace	intensive	propulsion	A rocket launched straight up has an initial mass of 60 t and burns 40 t of propellant at 300 kg/s with an exhaust velocity of 2900 m/s. Including gravity losses at a constant 9.81 m/s² and ignoring drag, what is its speed at burnout, in meters per second?	1,877.975637	m/s	0.01	t = 40000/300 s, v = ve ln(m0/mf) - g t
ae-l-i07	aerospace	intensive	orbits	A satellite in a circular orbit takes 6 hours per revolution. What is its altitude above Earth's surface, in kilometers? Use GM = 3.986e14 m³/s² and an Earth radius of 6371 km.	10,392.383734	km	0.01	r = (GM T^2 / 4 pi^2)^(1/3), h = r - R
ae-l-i08	aerospace	intensive	propulsion	A rocket nozzle expands gas from a chamber temperature of 3300 K to an exit pressure that is 1.5% of the chamber pressure. The gas has a ratio of specific heats of 1.22 and R = 360 J/(kg·K), and the mass flow is 60 kg/s. Ignoring pressure thrust, what thrust does it produce, in kilonewtons?	158.716897	kN	0.01	ve from isentropic expansion, F = mdot ve
ae-l-i09	aerospace	intensive	flight-mechanics	A glider has the drag polar CD = 0.03 + 0.05 CL². Flying at its best lift-to-drag ratio in still air, how far can it glide from an altitude of 2000 m, in kilometers?	25.819889	km	0.01	(L/D)max = 1 / (2 sqrt(K CD0)), d = (L/D)max h
ae-l-i10	aerospace	intensive	orbits	A satellite in a circular orbit 800 km above Earth's surface changes its inclination by 8 degrees in a single burn. What delta-v does that take, in kilometers per second? Use GM = 3.986e14 m³/s² and an Earth radius of 6371 km.	1.040144	km/s	0.01	v = sqrt(GM/r), dv = 2 v sin(di/2)
ae-q-c01	aerospace	calm	flight-mechanics	An aircraft climbs from 2000 m to 5000 m in 10 minutes. What is its average rate of climb, in meters per second?	5	m/s	0.01	RC = dh / dt
ae-q-c02	aerospace	calm	propulsion	A rocket engine with a thrust of 1.2 MN burns propellant at 400 kg/s. Ignoring pressure thrust, what is its effective exhaust velocity, in meters per second?	3,000	m/s	0.01	ve = F / mdot
ae-q-c03	aerospace	calm	aerodynamics	An aircraft flies at Mach 0.8 where the speed of sound is 300 m/s. What is its airspeed, in meters per second?	240	m/s	0.01	v = M a
ae-q-c04	aerospace	calm	aerodynamics	A sailplane wing has a span of 18 m and a mean chord of 0.9 m. What is its aspect ratio (unitless)?	20		0.01	AR = b / c for a rectangular wing
ae-q-a01	aerospace	alert	aerodynamics	An aircraft flies at 250 m/s where the air density is 0.41 kg/m³. What dynamic pressure does it experience, in kilopascals?	12.8125	kPa	0.01	q = rho v^2 / 2, in kPa
ae-q-a02	aerospace	alert	flight-mechanics	An aircraft with a mass of 5000 kg and a wing area of 25 square meters flies level at 90 m/s in air of density 1.0 kg/m³. Taking g = 9.81 m/s², what lift coefficient does it need (unitless)?	0.484444		0.01	CL = 2 m g / (rho v^2 S)
ae-q-a03	aerospace	alert	orbits	A satellite is in a circular orbit 600 km above Earth's surface. What is its orbital period, in minutes? Use GM = 3.986e14 m³/s² and an Earth radius of 6371 km.	96.538955	min	0.01	r = R + h, T = 2 pi sqrt(r^3 / GM)
ae-q-a04	aerospace	alert	propulsion	A spacecraft with a dry mass of 2000 kg carries 1500 kg of propellant for an engine with a specific impulse of 310 s. Taking g0 = 9.80665 m/s², what is its ideal delta-v, in meters per second?	1,701.266412	m/s	0.01	dv = Isp g0 ln((dry + prop) / dry)
ae-q-i01	aerospace	intensive	orbits	A spacecraft in a circular orbit 300 km above Earth fires its engine once to enter an elliptical orbit with its perigee there and its apogee 2000 km above Earth. What delta-v does that burn take, in meters per second? Use GM = 3.986e14 m³/s² and an Earth radius of 6371 km.	425.114091	m/s	0.01	a = (r1 + r2) / 2, vp from vis-viva, dv = vp - v_circ
ae-q-i02	aerospace	intensive	aerodynamics	An aircraft flies at 270 m/s where the air temperature is 220 K. With a ratio of specific heats of 1.4 and R = 287 J/(kg·K), what is the ratio of stagnation temperature to static temperature (unitless)?	1.16494		0.01	a = sqrt(g R T), M = v / a, T0/T = 1 + (g-1)/2 M^2
ae-q-i03	aerospace	intensive	flight-mechanics	An aircraft weighing 50 kN has a wing area of 30 square meters and the drag polar CD = 0.025 + 0.045 CL². At sea level, where the air density is 1.225 kg/m³, at what speed is its lift-to-drag ratio highest, in meters per second?	60.421215	m/s	0.01	CL* = sqrt(CD0 / K), V = sqrt(2 W / (rho S CL*))
ae-q-i04	aerospace	intensive	propulsion	A jet engine takes in 80 kg/s of air at a flight speed of 220 m/s and exhausts it at 600 m/s. Ignoring fuel mass and pressure thrust, what thrust power does it deliver to the aircraft, in megawatts?	6.688	MW	0.01	F = mdot (ve - v0) = 30.4 kN, P = F v0
aho-c1	null	calm	null	What is the Mach number of a jet flying at 600 m/s where the speed of sound is 300 m/s (unitless)?	null	null	null	null
aho-c2	null	calm	null	A rocket engine has a specific impulse of 450 s. Taking g0 = 9.80665 m/s², what is its exhaust velocity, in meters per second?	null	null	null	null
aho-c3	null	calm	null	What is the air pressure at sea level in the International Standard Atmosphere, in pascals?	null	null	null	null
aho-c4	null	calm	null	An aircraft weighing 80000 N has a wing area of 40 square meters. What is its wing loading, in pascals?	null	null	null	null
aho-c5	null	calm	null	A rocket expels 80 kg/s of propellant at 3200 m/s. Ignoring pressure thrust, what is its thrust, in kilonewtons?	null	null	null	null
aho-c6	null	calm	null	What is the load factor of an aircraft in a level turn at a 45 degree bank angle (unitless)?	null	null	null	null
aho-c7	null	calm	null	A 2 kg drone hovers in place. Taking g = 9.81 m/s², what total thrust do its rotors produce, in newtons?	null	null	null	null
aho-c8	null	calm	null	What is the escape velocity from the surface of the Moon, in kilometers per second?	null	null	null	null
aho-a1	null	alert	null	An aircraft with a wing area of 28 square meters flies at 75 m/s in air with a density of 1.0 kg/m³, at a lift coefficient of 0.45. What lift does the wing produce, in newtons?	null	null	null	null
aho-a2	null	alert	null	What is the speed of a satellite in a circular orbit 800 km above Earth, in kilometers per second? Use GM = 3.986e14 m³/s² and an Earth radius of 6371 km.	null	null	null	null
aho-a3	null	alert	null	A rocket with a specific impulse of 330 s has a mass ratio of 5. Taking g0 = 9.80665 m/s², what is its ideal delta-v, in meters per second?	null	null	null	null
aho-a4	null	alert	null	What is the speed of sound in air at 250 K, in meters per second, with a ratio of specific heats of 1.4 and R = 287 J/(kg·K)?	null	null	null	null
aho-a5	null	alert	null	A glider with a lift-to-drag ratio of 30 glides in still air from an altitude of 1500 m. How far does it travel over the ground, in kilometers?	null	null	null	null
aho-a6	null	alert	null	Air at 300 K is compressed isentropically by a pressure ratio of 8. With a ratio of specific heats of 1.4, what is its temperature after compression, in kelvin?	null	null	null	null
aho-a7	null	alert	null	An airplane makes a level turn at 120 m/s with a 45 degree bank. Taking g = 9.81 m/s², what is its turn radius, in meters?	null	null	null	null
aho-a8	null	alert	null	What is the period of a circular orbit 1000 km above Earth, in minutes? Use GM = 3.986e14 m³/s² and an Earth radius of 6371 km.	null	null	null	null
aho-i1	null	intensive	null	What total delta-v does a Hohmann transfer from a 400 km circular orbit to a 2000 km circular orbit take, in kilometers per second? Use GM = 3.986e14 m³/s² and an Earth radius of 6371 km.	null	null	null	null
aho-i2	null	intensive	null	A two-stage rocket lifts off at 80 t. Stage 1 burns 55 t of propellant at a specific impulse of 290 s and drops 8 t of dry mass; stage 2 then burns 12 t of propellant at a specific impulse of 330 s. Taking g0 = 9.80665 m/s², what is the total ideal delta-v, in meters per second?	null	null	null	null
aho-i3	null	intensive	null	An aircraft weighing 200 kN with a wing area of 100 square meters flies level at 150 m/s where the air density is 0.9 kg/m³. With a drag polar CD = 0.025 + 0.05 CL², what thrust does it need, in kilonewtons?	null	null	null	null
aho-i4	null	intensive	null	A spacecraft with a dry mass of 5000 kg needs 2500 m/s of delta-v from an engine with a specific impulse of 300 s. Taking g0 = 9.80665 m/s², how much propellant does it need, in kilograms?	null	null	null	null
aho-i5	null	intensive	null	An aircraft flies at 600 m/s where the air temperature is 223 K. With a ratio of specific heats of 1.4 and R = 287 J/(kg·K), what is the stagnation temperature, in kelvin?	null	null	null	null
aho-i6	null	intensive	null	A satellite needs a circular orbit with a period of 6 hours. What altitude above Earth's surface does that take, in kilometers? Use GM = 3.986e14 m³/s² and an Earth radius of 6371 km.	null	null	null	null
aho-i7	null	intensive	null	A jet with a lift-to-drag ratio of 15 cruises at 230 m/s with a thrust-specific fuel consumption of 0.7 per hour, until its weight falls from 1.25 to 1.0 times its final weight. Using the Breguet range equation, how far does it fly, in kilometers?	null	null	null	null
aho-i8	null	intensive	null	A rocket launched straight up burns propellant for 120 s, going from 50 t to 20 t with an exhaust velocity of 2900 m/s. Including gravity losses at a constant 9.81 m/s² and ignoring drag, what is its speed at burnout, in meters per second?	null	null	null	null
ae-c01	aerospace	calm	aerodynamics	An aircraft flies at 255 m/s where the speed of sound is 340 m/s. What is its Mach number (unitless)?	0.75		0.01	M = v / a
ae-c02	aerospace	calm	flight-mechanics	What is the weight of a 1200 kg aircraft at a gravitational acceleration of 9.81 m/s², in newtons?	11,772	N	0.01	W = m g
ae-c03	aerospace	calm	units	An aircraft flies at 250 knots, where 1 knot is 0.5144 m/s. What is its airspeed in meters per second?	128.6	m/s	0.01	v = 250 * 0.5144
ae-c04	aerospace	calm	propulsion	A rocket engine has a specific impulse of 300 s. What is its effective exhaust velocity in meters per second, taking g0 = 9.80665 m/s²?	2,941.995	m/s	0.01	ve = Isp g0
ae-c05	aerospace	calm	atmosphere	What is the air density at sea level in the International Standard Atmosphere, in kilograms per cubic meter?	1.225	kg/m^3	0.01	ISA sea-level density
ae-c06	aerospace	calm	constants	What is standard gravitational acceleration g0, in meters per second squared?	9.80665	m/s^2	0.005	Defined value 9.80665
ae-c07	aerospace	calm	atmosphere	What is the speed of sound at sea level in the International Standard Atmosphere, in meters per second?	340.292287	m/s	0.01	ISA sea level: a = sqrt(gamma R T) = 340.3 m/s
ae-c08	aerospace	calm	flight-mechanics	An aircraft weighing 50000 N has a wing area of 25 square meters. What is its wing loading, in pascals?	2,000	Pa	0.01	W / S (N/m^2 = Pa)
ae-c09	aerospace	calm	aerodynamics	A wing has a span of 30 m and an area of 90 square meters. What is its aspect ratio (unitless)?	10		0.01	AR = b^2 / S
ae-c10	aerospace	calm	propulsion	A rocket engine expels 250 kg/s of propellant at an exhaust velocity of 2800 m/s. Ignoring pressure thrust, what is its thrust in kilonewtons?	700	kN	0.01	F = mdot ve
ae-c11	aerospace	calm	orbits	What is the escape velocity from Earth's surface, in kilometers per second?	11.186129	km/s	0.01	v = sqrt(2 GM / R) = 11.19 km/s
ae-c12	aerospace	calm	flight-mechanics	An aircraft weighing 60 kN has 300 kW of excess power. What is its rate of climb, in meters per second?	5	m/s	0.01	ROC = P_excess / W
ae-c13	aerospace	calm	orbits	A 1000 kg satellite moves at 7500 m/s. What is its kinetic energy, in joules?	28,125,000,000	J	0.01	E = m v^2 / 2

End of preview.

PLM orchestrator: eval sets and every model answer

Data behind ro-rbl/plm-orchestrator, a local router that sends engineering tasks to small Ollama models (Qwen3-4B, Qwen3-8B, Qwen2.5-Coder-14B) in checkable domain packs: electrical, aerospace, physics, software, SQL and CAD.

eval_sets/: the project's own problem sets, with answer keys computed in code: electrical, aerospace and physics problems with numeric answers and units; software tasks with hidden tests; SQL tasks with reference queries; CAD parts with sizes and volumes; routing and level hold-out cases, including routing cases for a server given a database (router/sqldb_*). Several "fresh" sets were written before the experiment they judged.
results/: every saved model answer from every sweep and benchmark run, one JSONL line per task, with the grade, the pack's key-free check result and token counts. The routing simulations replay these files.
RESULTS.md: the headline table and the comparison with published scores.

Caveats

Every problem in eval_sets/ was written by Claude (an AI model), except router/sqldb_spider.jsonl and router/sqldb_schemas.json: 120 Spider dev questions and 20 Spider schemas, unchanged, by Tao Yu et al., CC BY-SA 4.0, and those two files stay under that license. Hold-outs guard against tuning to the test, not against author bias. The public-benchmark runs are the independent check.
Results on public benchmarks include model answers to those benchmarks' questions, not the questions: Spider dev, test and train (CC BY-SA 4.0), BIRD mini-dev and dev (CC BY-SA 4.0), UGPhysics, HumanEval+ and MBPP+ (EvalPlus; HumanEval MIT, MBPP CC BY 4.0), SciBench (MIT), TheoremQA (MIT), GSM8K (MIT), CADPrompt (no license stated; only our models' answers are included, no CADPrompt data). Use those results under the original benchmarks' terms.
Models ran locally through Ollama at temperature 0 on a 24 GB Apple-silicon Mac; compute is measured as model size times generated tokens, not wall time.

License

The eval sets and code-side data are MIT (see the repository), except the two Spider files above (CC BY-SA 4.0). Results on third-party benchmarks follow the note above.

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PLM orchestrator: eval sets and every model answer

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