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 ___________
Questionaircraft-design-questions-answers7.jpg
  • 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
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