Coefficients of lift, drag and pitching moment are given at zero yaw; coefficients of rolling moment, yawing moment, and side force given for rectangular wing at all values of yaw tested; results discussed.
Wind-tunnel investigations of effect of yaw on lateral-stability characteristics. I: four N.A.C.A. 23012 wings of various plan forms with and without dihedral
Nat Advisory Committee Aeronautics -- Tech Note
1939
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Englisch
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Pressure distribution over N.A.C.A. 23012 airfoil with N.A.C.A. 23012 external-airfoil flap
Engineering Index Backfile | 1938
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