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Aircraft Design Practice Test: Stability, Control, and Handling Qualities
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Stability, Control, and Handling Qualities topics include: Longitudinal and lateral-directional static stability and control, stick free and dynamic stability. Aircraft stability, control, and handling qualities are all related to the operation of an aircraft: Stability: An aircraft's ability to return to its original flight path, even when disturbed. Stability allows an aircraft to maintain uniform flight conditions, minimize pilot workload, and recover from disturbances. Control: An aircraft's ability to change its flight direction and attitude. Aircraft control describes the pilot's... Show more
Aircraft Design Practice Test: Stability, Control, and Handling Qualities
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25 Questions

1. How can we say that the aircraft has initial tendency to return to its original equilibrium position after being disturbed?
2. Which of the following is correct?
3. Stability about roll axis is called _____________
4. Determine sideslip angle for a steady level unaccelerated flight with [u, v, w] = [80, 2, 4.5].
5. An aircraft is consider to be over damped. What will be the appropriate value for damping ratio?
6. Which of the aircraft will be statically stable based on following diagram?
Following diagram represents ________
"For pitching moment coefficient diagram shown below which one will have positive trim AOA?"
7. An aircraft experiences sideslip of 4° and side wash at vertical tail is 1.2°. What will be the AOA at vertical tail?
8. Stick free stability permits ____________
9. A rectangular wing has chord of 2m. Fond neutral point for this wing.
10. Hinge moment coefficient depends upon ________
11. If SM = 0.12 and cg is located at 20% chord from l.e. then, find appropriate neutral point location.
12. An aircraft wing is experiencing AOA of 5°. If downwash due to wing is 2.6° then, how much angle is being seen by tail of the aircraft?
13. Canard will provide longitudinal static stability.
14. Which of the following is correct?
15. Determine the value of rudder deflection δr for an aircraft which is flying in north with the velocity of 60.5 m/s under the crosswind of 5m/s from east to west with Cnβ=0.02/deg and Cnδr = -0.045/deg, where sideslip angle β is -4.72°.
16. If CM0 is -0.052 and lift coefficient at zero angle CL0 is 0.92 then, find CMac. Consider rectangular wing.
17. If aircraft is in straight flight (cruise with lift of 100N) then, what will be the value of net rolling moment? Consider ideal conditions.
18. Determine the net velocity if sideslip angle is 3.8 degree and [v] = 4.2 unit.
19. Longitudinal stability means __________
20. Which of the following is not the type of aircraft dynamic mode?
21. Determine trim angle if, trim lift coefficient is 0.75 and lift curve slope is 4.5per rad. Consider elevator deflection as 1.056 per rad and trim elevator angle of 0.020 rad.
22. Yawing moment is positive if __________
23. Rolling moment will influence _______
24. If damping ratio is 0.05 then, find the lift to drag ratio. Consider 2-degree phugoid approximation.
25. Find the degree of elevator float. Consider tail AOA is 2° and CHδe= -0.005, CHɑt=-0.0052.