항공사 기출문제 정리 14

1. Upon landing, spoilers

 

a. decrease directional stability on the landing rollout

b. function by increasing tire to ground friction

c. should be extended after the thrust reversers have been deployed

 

2. One method of boundary layer control is accomplished by injecting

 

a. a jet of air into the leading edge to energize the boundary layer

b. a low speed jet of air into the boundary layer

c. a high speed jet of air into the boundary layer

 

3. On most airplanes, the first 50% of flap deflection causes

 

a. less than 50% of the total change in lift

b. more than 50% of the total change in lift

c. linear lift increases at the AFM specified speed

 

4. Swept wings causes a significant

 

a. increase in effectiveness of flaps

b. reduction in effectiveness of flaps

c. flap actuation reliability issue

 

5. Compared to a straight wing, swept wing flaps are

 

a. as effective

b. less effective

c. more effective

 

5. It is important to combine the boundary layer control with flaps since

 

a. the flap deflection tends to reduce the angle of attack for maximum lift

b. the flap deflection tends to increase the angle of attack for maximum lift

c. the boundary layer controls are only effective at low power settings

 

6. Leading-edge, high lift devices are

 

a. more effective on the highly swept wing than trailing edge flaps

b. less effective than a trailing edge device on a swept wing

c. more effective than flaps because of the increase in drag at relatively low angles of attack

 

7. What true airspeed and angle of attack should be used to generate the same amount of lift as altitude is increased?

 

a. The same true airspeed and angle of attack

b. A higher true airspeed for any given angle of attack

c. A lower true airspeed and higher angle of attack

 

8. How can an airplane produce the same lift in ground effect as when out of ground effect?

 

a. The same angle of attack

b. A lower angle of attack

c. A higher angle of attack

 

9. In a jet powered airplane (fan or pure jet) the angle of attack at stall is

 

a. variable only with altitude

b. very different from power on and power off

c. essentially the same power on or power off

 

10. An increase in airspeed above the stall speed will require

 

a. a relative decrease in the relative wind

b. a corresponding decrease in angle of attack and co-efficient of lift

c. a corresponding increase in co-efficient of lift and drag

 

11. Lift coefficient must be maximum at the

 

a. airplane stall speed

b. airplane maximum maneuvering speed

c. maximum mach operating limit

 

12. When at high angle of attack the boundary layer tends to

 

a. stagnate and stop

b. loop around the upper camber line

c. decrease air pressure along the chord

 

13. Propeller driven airplanes can develop more lift at slower airspeeds with high power on because

 

a. the dynamic pressure is created downstream of the propellers

b. the high power conditions decreases the maximum lift angle of attack

c. the high power reduces the lift required from the wings

 

14. At the end of a power-on approach in a propeller driven airplane, if the pilot sharply reduces power,

 

a. the airplane may continue to float for a long distance down the runway

b. the airplane may drop suddenly due to reduced lift

c. the airplane's engine will quit running if the power is reduced suddenly

 

15. A bank angle of 15˚ will increase induced drag by about

 

a. 3%

b. 7%

c. 15%

 

16. A bank angle of 30˚ will increase induced drag by about

 

a. 18%

b. 33%

c. 24%

 

17. A bank angle of 45˚ will increase induced drag by about

 

a. 33%

b. 100%

c. 76%

 

18. A bank angle of 60˚ will increase induced drag by about

 

a. 200%

b. 300%

c. 100%

 

19. Which is a purpose of wing-mounted vortex generators?

 

a. Reduce the drag caused by supersonic flow over portions of the wing

b. Increase the onset of drag divergence and aid in aileron effectiveness at high speed

c. Break the airflow over the wing so the stall will progress from the root out to the tip of the wing

 

20. Airflow separation over the wing can be delayed by using vortex generators

 

a. directing high pressure air over the top of the wing or flap through slots and making the wing surface smooth

b. directing a suction over the top of the wing or flap through slots and making the wing surface smooth

c. making the wing surface rough and/or directing high pressure air over the top of the wing or flap through slots

 

21. An airplane stall warning device must sense

 

a. relative wind

b. coincident wind

c. angle of attack

 

22. How does Vs (KTAS) speed vary with altitude?

 

a. Remains the same at all altitudes

b. Varies directly with altitude

c. Varies inversely with altitude

 

23. How does Vne Change with altitude?

 

a. remains the same at all altitudes

b. varies inversely with altitude

c. varies directly with altitude

 

24. At which speed will increasing the pitch attitude cause an airplane to climb?

 

a. Low speed

b. High speed

c. Any speed

 

25. What effect does an increase in airspeed have on a coordinated turn while maintaining a constant angle of bank and altitude?

 

a. The rate of turn will decrease resulting in a decreased load factor

b. The rate of turn will increase resulting in an increased load factor

c. The rate of turn will decrease resulting in no changes in load factor

 

26. During a skidding turn to the right, what is the relationship between the component of lift and centrifugal force?

 

a. Centrifugal force is less than the horizontal lift component, and the load factor is increased

b. Centrifugal force is greater than the horizontal lift component

c. Centrifugal force and the horizontal lift component are equal, and the load factor is decreased

 

27. What is the relationship of the rate of turn with the radius of turn with a constant angle of bank but increasing airspeed?

 

a. Rate will decrease and radius will increase

b. Rate will increase and radius will decrease

c. Rate and radius will increase

 

28. Generally, the turning performance of an airplane is defined by

 

a. structural and power limits at high altitude

b. aerodynamic and structural limits at low altitude

c. control and structural limits at high altitude

 

29. An increase in airspeed followed by a decrease in control effectiveness may result in

 

a. a decrease in downwash on the horizontal tail, resulting in a "tuck under"

b. an increase in downwash on the horizontal tail, resulting in a "tuck under"

c. the need for retrimming due to the increase speed

 

30. Describe dynamic longitudinal stability

 

a. Motion about the longitudinal axis

b. Motion about the lateral axis

c. Motion about the vertical axis