Q.1.
Stability about yawing axis is called as __________
- a) directional stability
- b) lateral stability
- c) longitudinal stability
- d) pitching moment stability
Q.2.
Yawing moment is positive if __________
- a) right wing goes back
- b) right wing comes forward
- c) if nose pitches up
- d) if nose pitches down
Q.3.
Stability about roll axis is called _____________
- a) lateral stability
- b) directional stability
- c) longitudinal stability
- d) elevator control
Q.4.
If aircraft is in straight flight (cruise with lift of 100N) then, what will be the value of net rolling moment? Consider ideal conditions.
- a) 0 unit
- b) 12 Nm
- c) 23 unit
- d) 25 N/m
Q.5.
Which is the minimum requirement for pure directional stability?
- a) Slope of yawing moment curve positive
- b) Negative lift curve slope
- c) Negative pitching moment coefficient curve slope
- d) Positive zero lift pitching moment coefficient
Q.6.
Rolling moment will influence _______
- a) aircraft lateral stability
- b) longitudinal stability
- c) pitch axis stability
- d) pitching stability only
Q.7.
Following diagram represents ___________
- a) typical roll stability concept
- b) typical longitudinal stability
- c) lift curve
- d) drag polar
Q.8.
An aircraft experiences sideslip ofand side wash at vertical tail is 1.2°. What will be the AOA at vertical tail?
- a) 5.2°
- b) 6.89°
- c) 1.2°
- d) 21.3°
Q.9.
Aircraft can suffer from adverse yaw during rolling.
- a) True
- b) False
Q.10.
An aircraft is flying in the north direction at a velocity of 60.5m/s under cross wind from the east to west of 5m/s. If the value of Cnβ=0.02/deg, where. Find sideslip angle β.
- a) -4.72°
- b) -5°
- c) 4.7°
- d) 3.18°
Q.11.
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°.
- a) -2.09°
- b) 3.5°
- c) -4.5°
- d) -4.74°
Q.12.
Find sideslip angle if [u, v, w] = [2.5]. Consider steady level flight.
- a) 2.86°
- b) 4.5°
- c) 4.7°
- d) 2.1°
Q.13.
Find resultant velocity if [u, v, w] = [4.5]. Consider steady level flight.
- a) 80.151
- b) 90
- c) 10.52
- d) 100.159
Q.14.
Determine sideslip angle for a steady level unaccelerated flight with [u, v, w] = [4.5].
- a) 1.43
- b) 5.4
- c) 5
- d) 12.32
Q.15.
Determine the net velocity if sideslip angle is 3.8 degree and [v] = 4.2 unit.
- a) 63.23 unit
- b) 100 unit
- c) 100.23 unit
- d) 102.623 unit