Wind-tunnel investigation of effect of yawing on lateral-stability characteristics II : rectangular N.A.C.A. 23012 wing with a circular fuselage (1939)
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Figs.8,9 N.A.O.A. Tecnnical Rote Ho.730 .01 (mi) .003 /40J "\ .003 T.003 0 6 10 -10 -5 15 20 Angle of attack,a,deg. Figure 8.- Variation ofg ,(^)o>g/and gjft -ito u*U of attaok. Oiroulax fuselage wita and without fin.
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