Aerospace Engineering > GATE 2010 > Longitudinal Stability
The trim curves of an aircraft are of the form Cm,...=(0.05-0.2δ)
-0.1CL where the elevator
deflection angle, δc, is in radians. The change in elevator deflection needed to increase the lift
coefficient from 0.4 to 0.9 is:
A
-0.5 radians
B
-0.25 radians
C
0.25 radians
D
0.5 radians

Correct : b

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Related Topics

GATE Aerospace Engineering 2010 GATE AE 2010 Q44 aircraft trim curves elevator deflection angle lift coefficient elevator deflection aircraft flight mechanics pitch stability and control

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