Wind tunnel research comparing lateral control devices, particularly at high angles of attack XI : various floating tip ailerons on both rectangular and tapered wings (1933)
NASA Technical Reports Server (NTRS) · leaf 36
N.A.C.A. Technical JTote "So. 458 Fig. 9 .07 … 0 fC 1 1 1 i 1 1 1 1 00 10° 20° 30° 40° 500 Difference in angle of ailerons, 6 Figure 9. Variation of rolling moment coefficient with, aileron deflection for the tip ailerons on the taiDered wings, a, = 10°
NASA Technical Reports Server (NTRS)
Internet Archive · NASA Technical Reports · Public domain (US government work). Free to use for anything.
