Validation of the Approximate Calculation Procedure HOTSOSE For Aerodynamic and Thermal Loads in Hypersonic Flow with Existing Experimental and Numerical Results

Abstract

The approximate method HOTSOSE has been developed to predict aerodynamic and thermal loads within the predesign stage of hypersonic vehicles, using either perfect gas or equilibrium air. HOTSOSE is based on surface inclination methods to determine the pressure and serveral approximate methods to evaluate heat transfer. In the present work the HOTSOSE code has been validated for a variety of configurations. Both total and local aerodynamic coefficients and local heat transfer coefficients obtained from HOTSOSE are compared with Euler- and Navier-Stokes solutions, covering the influences of Mach number, angle of attack, gas model and boundary layer state. The HOTSOSE results show reasonable or good agreement with the reference solutions in most cases. Therefore, HOTSOSE is an efficient tool for rapid computations of aerodynamic forces and heat loads for complete configurations.