INVESTIGATION AT MACH NUMBERS FROM 0.80 TO 1.43 OF PRESSURE AND LOAD DISTRIBUTIONS OVER A THIN 45° SWEPTBACK HIGHLY TAPERED WING IN COMBINATION WITH BASIC AND-INDENTED BODIES

摘要

Pressure distributions have been obtained in the Langley 8-foot transonic tunnels over a Mach number range from 0.80 to 1.125 and at a Mach number of 1.4-3 for a ^5° sweptback cambered wing having a thickened root, an aspect ratio of 4.0, and a taper ratio of 0.15. Data were obtained for the wing in the presence of a basic Sears-Haack body and a body indented symmetrically for a Mach number of 1.2.