Aerospace Engineering > GATE 2020 > Stability and Control
For conventional airplanes, which one of the following is true regarding roll control derivative (Clδr = ∂Cl/∂δr) and yaw control derivative (Cnδr = ∂Cn/∂δr), where δr is rudder deflection?
A
Clδr > 0 and Cnδr < 0
B
Clδr < 0 and Cnδr > 0
C
Clδr < 0 and Cnδr < 0
D
Clδr > 0 and Cnδr > 0

Correct : a

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airplane control derivatives roll control derivative yaw control derivative aerospace engineering gate control derivatives aircraft rudder deflection control aircraft control equations GATE Aerospace Engineering 2020

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