AERODYNAMIC STUDY - FORCE AND MOMENT MEASUREMENTS ON THREE DELTA WINGS OF ASPECT RATIOS 0.83, 1.03 AND 1.24 IN COMBINATION WITH BODIES OF FINENESS RATIO 13 AT A MACH NUMBER OF 4

摘要

Force measurements have been made in the High Supersonic Speed Wind Tunnel on a series of wing-body configurations at a Mach number of 4 and Reynolds number of 32 x 106. The combinations tested consisted of circular section bodies of fineness ratio 13 and delta wings of aspect ratios 0.83, 1.03 and 1.24. The wing span of all combinations was 5 body diameters.nLift and pitching moment variations with incidence were found to be reasonably linear up to 20°, which was the limit of the present tests. The highest lift/drag ratio was obtained with the lowest aspect ratio wing, giving a figure of 5.7 for a 3 calibre ogival nose on the body and 6.2 for a 5 calibre nose. It was found that the force and moment charac-teristics could in general be predicted adequately from existing theories, the main exception being the rolling moment due to sideslip.