An approximate spin design criterion for monoplanes (1939)
NASA Technical Reports Server (NTRS) · leaf 8
H.A.C.A. Technical Sote Ho. 711 Figs. 1,9 r s u v a c e n … section to eg of airplane Fin Area under tail plane Body Body damping ratio - A^X]2* A3x32 » A12xx32 ♦ 3(A15xi32 » A16X162) ♦ A17x173 + A30x303 S(b/3)< 3, wing area b/3, semispan Shaded areas x Unshielded rudder volume coefficient Gross wing area b/3 Figure 1.- Method of computation of damping…
NASA Technical Reports Server (NTRS)
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