Consider an airplane with rectangular straight wing at dihedral angle $\Gamma=10^{\circ} .$ Lift curve slope of wing airfoil section (constant over the whole span of the wing) is $c_{l \alpha}=5.4 / \mathrm{rad}$. The roll stability derivative, $C_{l \beta}$ in per radian is________________

Question ID - 156026 | SaraNextGen Top Answer

Consider an airplane with rectangular straight wing at dihedral angle $\Gamma=10^{\circ} .$ Lift curve slope of wing airfoil section (constant over the whole span of the wing) is $c_{l \alpha}=5.4 / \mathrm{rad}$. The roll stability derivative, $C_{l \beta}$ in per radian is________________