Pitching moment derivatives have been measured by a free oscillation technique on wings of rectangular planform and of double wedge section with a thictiess/chord ratio of 0.12. The wings of aspect ratio 1, 2, 3, 4 and 5 were oscillated about the half-chord axis in flows of Mach number 1.79, PI5 and 2.43. The Reynolds number and frequency parameter of the tests were less than I @ and 0.03 respectively. Tunnel boundary-layer effects were avoided by the use of a reflection plate. The influence of a body (non-oscillating) with various nose shapes was also investigated. On the plain wings it was found that the general trend of the variation with aspect ratio was predicted by theory but the numerical values differed considerably. The presence of a body tended to reduce the value of the damping derivative. I
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