Heat transfer and boundary layer growth for ultra high Reynolds number compressible turbulent boundary layers for a radiatively driven hypersonic wind tunnel
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Although the Radiatively Driven Hypersonic Wind-Tunnel concept overcomes the need for very high reservoir temperatures for a hypersonic test facility that simulates true flight conditions, the heat transfer rate to the nozzle wall remains a critical design issue. The purpose of the present work is to develop and assess a numerical model to simulate ultra high Reynolds number, Re/m~1010, compressible, turbulent boundary layer flows taking into consideration the effects of surface roughness. The twodimensional Reynolds Averaged Navier Stokes equations are used along with the Baldwin-Lomax formulation of the turbulence model with the eddy viscosity modified to include surface roughness based on the model of Rotta. All thermodynamic properties are based on the NIST equation of state (NIST14) for air. The predictions are compared with experimental results for supersonic boundary layers at a Reynolds number of 107/m over a flat plate for different wall roughness. Numerical results are then obtained for a Mach 2.75 boundary layer on a flat plate at a Reynolds number of 1010and then predictions are presented and comparisons made with preliminary results obtained at a comparable ultra high Reynolds number in a blow down facility operated at a stagnation pressure of 30,000psi. These experiments are being conducted in parallel with the numerical modeling. 2002 by Princeton University.
