Gun Tunnel Measurements of Lift, Drag and pitching Moment on a 20° Cone, a Flat Delta and a Caret Delta Wing at a Mach number of 8.3

摘要

Measurements of lift drag and pitching moment have been made on a 20° half-angle, right-circular cone end on two delta wings of triengular and caret cross section, 10° wedge angle and aspect ratio 1 in the Imperial College gun tunnel.nThe strain gauge balance developed for this purpose gave results which were within 5% of other published cone data.nMaximum lift/drag ratios of about 3.7 were obtained for both wings at the test Mach number of 8.3 and Reynolds number based, on root chord of 1.5 X 106.