Wind-tunnel investigation of effect of yawing on lateral-stability characteristics II : rectangular N.A.C.A. 23012 wing with a circular fuselage (1939)
NASA Technical Reports Server (NTRS) · leaf 15
Figs.10,11 tf.A.C.A. Technioal Mote Ho.?30 .006 -.003 -.004. 6 10 Angle of attack,a,leg. Figure 10.- Variation of with angle of attack. Rectangular N.A.O.A. 33012 wing alone and in combination with circular fuselage with and without fin; 6f,0°; r,5°. … Angle of attaolc.a.deg. — —, —, 0- Figure 11.- Variation of^^ gwitl1 "S16 of attaok' Rectangular H.A.O.A. 23013 wing alone and in combination with circular fuselage with and without fin; 6f,60°; r,0°.
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