Shuttle elevon cove aerodynamic heating by internal flow

Abstract

The thermal response of the cove seal area of the Shuttle elevon wing junction is investigated in an arc heated supersonic duct. The temperature response of the seal area is measured for various seal gap widths, ambient pressures, and enthalpies to determine the dependence of internal heating on these parameters. A correlation of the results shows that the internal heating to the seal is proportional to the product of the external pressure, the gap width and the square root of the total enthalphy. Temperatures at the end of a simulated Shuttle entry compare well with predictions based on this correlation for the narrower gap widths where there is only a small pressure drop at the cove inlet. Similar predictions are made for Shuttle flight as a function of seal gap widths to determine the maximum gap width allowable, yet not exceed design temperatures on the structure.