Aerospace Engineering > GATE 2019 > Aircraft Stability
The design of an airplane is modified to increase the vertical tail area by 20% and decrease the moment arm from the aerodynamic centre of the vertical tail to the airplane centre of gravity by 20%. Assuming all other factors remain unchanged, the ratio of the modified to the original directional static stability (C_N_β due to tail fin) is _______ (round off to 2 decimal places).
Correct : 0.96 to 0.96
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