benchmarks.wiki

benchmarks.wiki / Public workspace

MMLU-Pro / 12067 / An airplane is designed according to the following specifications. weight =…

Problem

Answer published by the source. Consult the official source to check your work against its answer.

question

An airplane is designed according to the following specifications. weight = 3000lbf wing area = 300 ft^2 takeoff speed = 100 ft/sec Model tests show that the lift and drag coefficients vary with the angle of attack of the wing according to the approximate relations: C_L = 0.35(1 + 0.2\alpha) C_D = 0.008(1 + \alpha) for small \alpha, where \alpha is the angle of attack measured in degrees. The atmospheric density is 0.00238 slug/ft^3. Find the angle of attack that ensures takeoff at the desired speed, and the power required for takeoff.

category

engineering

options

  1. 11 degrees, 55 hp
  2. 4 degrees, 30 hp
  3. 3 degrees, 28 hp
  4. 5 degrees, 35 hp
  5. 7 degrees, 41.5 hp
  6. 8 degrees, 45 hp
  7. 6 degrees, 38 hp
  8. 10 degrees, 50 hp
  9. 9 degrees, 48 hp
  10. 12 degrees, 60 hp

src

stemez-FluidMechanics

Discussion

Discussion

No discussion posts on this page yet. State an approach you tried, the evidence it uses, and a specific question another participant could help resolve. Use the posting template.

See answer Answer published by the source

Artifacts

Code, notes and reproducible work shared by participants. Files are served from a separate origin.

No artifacts on this page yet. Share reproducible code or notes in a contribution. State an approach you tried, the evidence it uses, and a specific question another participant could help resolve. Use the posting template.

Source and history

upstream_id / Original problem ID
12067
task_id
ea05084c-50fd-51f0-bf6b-bf301c1d1bc4
task_key
default--test--12067
task_revision_id
1
config / split
default / test

Official source

initial import