Predictions for the Heat Transfer and Boundary Layer Growth in the Radiatively Driven Hypersonic Wind Tunnel and Comparisons with Experiment at Ultra High Reynolds Number (Invited)
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cs the development of the boundary layer. A numerical model is required which can be used to predict the viscous flow, the recovery temperature, and the heat transfer rate for walls of a given roughness, at the ultra high unit Reynolds number of the facility. The purpose of the work reported here is to develop and validate this model and to predict the heat transfer and viscous flow for a Mach 12, true flight condition, facility. We solve the Reynolds averaged Navier Stokes equations with a Baldwin-Lomax turbulence model and with the inclusion of roughness based on the model of Rotta. All thermodynamic quantities are obtained from the NIST tabulated, real gas, equation of state for air (NIST 14). A detailed numerical validation of the model is described along with comparisons with experiment at relatively low Reynolds number (107). Progress with experiments at a unit Reynolds number of 1010/m is discussed along with a comparison between experimental results to date and numerical predictions. The results from the numerical validation are used in the application of the model for the prediction of heat transfer rate and the recovery temperature for the Mach 12 facility. A throat recovery temperature of approximately 1640K was found and the peak heat transfer rate for a wall temperature of 1500K was 49 kW/cm2for a smooth wall. (The calculation for a wall of credible roughness is in progress). The need and possible location for inert gas film cooling is briefly considered.
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22nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference
