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Aircraft Design
Aircraft Design Objective
Quiz 1
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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
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