Heat Transfer Measurements On Waverider at Hypersonic Mach Numbers

Abstract

Waveriderwhich with its geometry designed for a specific Mach number optimally exploits the lift generated due to shock wavesis a promising aerodynamic configuration for hypersonic flight. A conically derived waverider is designed for a nominal Mach number of 6. Detailed aerodynamic tests on the designed wave rider are initiated. Since hypersonic flows are essentially characterized by high flow total enthalpies, their simulations require impulse facilities like shock tunnels. Experiments are performed in IISc Hypersonic Shock tunnel HST-2 at the design Mach number as well as at an offdesign Mach number of 8, with a flow total enthalpy of 2 MJ/kg. Heat transfer rates are important concern at such high total enthalpies. The surface heat transfer distribution on the waverider at design and off-design conditions, measured using platinum thin film sensors, are presented in this paper. Despite the same flow total enthalpy, higher heat transfer rates are observed at Mach 6 than at Mach 8.