Pressure Plotting and Balance Measurements in the High Speed Wind Tunnel on a Half-model of a 90-deg-Apex Delta Wing with Fuselage

摘要

Tests were made at a Reynolds number of 1-8 X 106 and Mach numbers up to 0.93. The wing tip was cropped to a taper of 1/7 and the wing section was RAE 102, symmetrical, 10 per cent thickness/chord at 35 per cent chord.nForm drag is highly localised near the root at low speed. Above M = 0-88, rearward movement of the strong shock causes a rapid rise of drag at all sections.