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Question
Consider an airplane with rectangular straight wing at dihedral angle T = 100 . Lift curve slope of wing airfoil section (constant over the whole span of the wing) is cla = 5.4/rad. The roll stability derivative, Clb in per radian is __________
Options:
A .  0.25 to 0.26
B .  -0.25 to -0.26
C .  0.23 to 0.24
D .  -0.23 to -0.24
Answer: Option D


-NA-



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