Surface-flow, pressure, and heat-transfer studies on two conical delta wings at a Mach number of 6

An experimental investigation of the surface flow, pressures, and heat transfer on two conical delta wings having attached leading-edge shocks has been conducted at a Mach number of 6. The angle of attack was varied between 0 deg and 12 deg. The pressure data were compared with predictions obtained by the method-of-lines technique, and the heating data were compared with the heating levels predicted by the Spalding-Chi method.