Abstract
Wavecatcher (inward-turning) intake flows, at design Mach 12, are investigated numerically, to display the effect of wall temperature on flow structures and intake performance. Hypersonic experiments on shock wave/boundary layer interaction are used to validate the Spalart-Allmaras turbulence model for reproducing the features of hypersonic flow. Simulations of hypersonic intake flow are performed at different wall temperatures, including isothermal Tw = 300 K, Tw = 1000 K, Tw = 2000 K, and the adiabatic case. The shock structures, impinging shock positions, surface streamlines, and the development of internal streamwise vortices are discussed. The mass-averaged performance of intake flow shows that, when the wall temperature changes from Tw = 300 K to adiabatic, the mass capture coefficient decreases from 0.991 to 0.933, the total pressure recovery decreases from 0.200 to 0.083, while exit section Mach number decreases from 4.478 to 3.514. The results suggest that the osculating design method of wavecatcher intake design can successfully be extended to Mach 12, while capturing all airflow at isothermal wall conditions.
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