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Aircraft Design Practice Test: Performance and Flight Mechanics
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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. Which of the following is correct in terms of fate of climb (R/C)?
2. Consider a glider is descending from 2km altitude. If it covers range of 30km then, at which aerodynamic efficiency the glider was flying?
3. Determine the value of fuel burned during steady climb if SFC C is 0.000029 per second, thrust is 150KN and time required is 1500s.
4. 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.
5. Which of the following is correct?
6. Which of the following is correct for steady level flight?
7. Determine the value of sink rate of glider which is operating with 4.2° of glide angle and has speed of 120m/s.
8. What do you mean by rate of climb?
9. Total energy of an aircraft is defined as ____________
10. Unit of specific energy is __________
11. The highest altitude where Ps is zero is called ________
12. Consider steady climb from an altitude of 10km to 15km. If rate of climb is 20 m/s then, determine the time to climb.
13. Which of the following is incorrect?
14. If KCD0 is 0.014 then, find lift to drag ratio for minimum sink.
15. If aerodynamic efficiency of the glider is 20 then, found the value of corresponding glide angle.
16. During level turning operation my aircraft has load factor of 2. Find the required bank angle for this level turning operation.
17. 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.
18. If my aircraft is in steady level flight and has thrust of 100 unit then, what will be the approximate value of time Easter if change of aircraft weight. Consider SFC as C unit.
19. Operating envelope is also known as ________
20. Find liftoff distance for an aircraft which has weight of 20kN and thrust of 8kN. Consider thrust is much larger than drag and friction parameters. Consider maximum lift coefficient of 1.1, reference area of 12m2 and sea-level density.
21. Determine the value of climb angle if, excess thrust is 40 unit and weight of the aircraft is 60 unit. Consider steady climb.
22. Find climb angle of climb gradient is 0.6. Assume non accelerated flight.
23. If Total energy of an aircraft is found to be 1200 unit and kinetic energy is 1100 unit then, determine the potential energy.
24. Find instantaneous range of a jet propelled aircraft if lift to drag ratio is 12 and weight fraction at cruise W1/W0 is 1.9. Consider cruise speed of 120m/s and SFC of 0.00161 per second.
25. If stall speed of the aircraft is 10m/s then, find the approximate value of takeoff speed.