Identification of heat-exchange processes in a supersonic spatial flow past aircraft

Direct and inverse problems of heat exchange in a supersonic spatial flow past the front part of an aircraft in the form of a spherically blunted nose cone have been solved numerically. The prospects of using high-heat-conductivity materials and the blowing of the gas-coolant for lowering the temperature on the surface of an aerodynamic body have been shown. A comparison of the solutions of the direct and inverse problems in one-, two-, and three-dimensional formulations for various materials of the sheath has been made. The error in recovering the heat flow by the thin-walled method has been estimated. © 2004 Plenum Publishing Corporation.