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 … 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°. .006 ~1 1 1 Wing location.High Kid Low Fin on + n > Fin off o v x Wing alone A. <> < -.003 5 10 Angle of…
NASA Technical Reports Server (NTRS)
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