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Aircraft Design Practice Test: Performance and Flight Mechanics
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Avg score: 0% Most missed: “A typical glider has weight of 150N and has glide angle of 2.5°. Find Lift produ…”
Performance and Flight Mechanics topics include: Steady level flight, steady climbing and descending flight, level turning and gliding flight, energy maneuverability methods, flight mechanics operating envelope, flight mechanics takeoff and landing analysis. Aircraft performance is a measure of how well an aircraft flies. It includes many factors such as:  Weight, Atmospheric conditions, Pressure, Temperature, Humidity, Runway at takeoff, Density altitude.  Aircraft performance can include: Speed Ceiling Range Fuel efficiency Take-off distance required Climb rate Aircraft... Show more
Aircraft Design Practice Test: Performance and Flight Mechanics
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25 Questions

1. If lift coefficient at thrust required minimum is 0.85 and induced drag factor K is 0.0085 then, find the approximate value of drag coefficient at zero lift.
2. In Steady level unaccelerated flight, lift is equal to weight.
3. If KCD0 is 0.014 then, find lift to drag ratio for minimum sink.
4. Which of the following is incorrect?
5. Find climb angle of climb gradient is 0.6. Assume non accelerated flight.
6. Determine the value of climb angle if, excess thrust is 40 unit and weight of the aircraft is 60 unit. Consider steady climb.
7. During level turning flight, lift of wing is canted.
8. If Total energy of an aircraft is found to be 1200 unit and kinetic energy is 1100 unit then, determine the potential energy.
9. Find lift to weight ratio if climb angle is 45°.
10. If a glider needs to be flown at maximum range then, at which value of CL we should fly this glider? Consider CD0/K is 2.8.
11. Which of the following is correct in terms of fate of climb (R/C)?
12. Let’s consider our aircraft has to generate thrust of 150KN during cruise. If at the cruise thrust loading is 0.86 then, at which value of Lift our aircraft is flying?
13. An aircraft is operating with CL of 1.5 and has power required of 120W. If we want to reduce the power required by half then, find the value of CL at this power required condition. Consider steady level flight.
14. If a Maneuver requires specific power of 1200 unit then, find the approximate value of fuel specific energy. Given thrust as 1000 unit and tsfc of 0.00042 unit.
15. A jet engine is designed to operate at endurance of 12hrs. If weight fraction is 1.6 and jet engine has tsfc C as 0.00021 per second then, find at which lift to drag ratio that can satisfy above criteria.
16. Consider external flow dynamic pressure as 2000psf and static pressure as 800psf. find the approximate value of Mach number.
17. Which of the following is correct?
18. Falling diagram represents _________
The level flight envelope is determined by ________"
19. Total energy of an aircraft is defined as ____________
20. The highest altitude where Ps is zero is called ________
21. Determine the value of sink rate of glider which is operating with 4.2° of glide angle and has speed of 120m/s.
22. Consider turning gliding flight. Turn rate is given as 0.2 unit and velocity of flight is 10 unit. Find the value of turn radius.
23. Total energy divided by the aircraft weight is term as ____________
24. An aircraft is designed with lift coefficient of 1.1 during steady level flight. If dynamic pressure is set to be 25.65 Pa then find weight of aircraft during this flight condition.
25. Graphical representation of sink rate of sailplane is called ____________