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The supersonic diffuser of a Mach 2.68 bifurcated, rectangular, mixed-compression inlet was analyzed using a two-dimensional (20) Navier-Stokes flow solver. Parametric studies were performed on turbulence models, computational grids and bleed models. The computed flowfield was substantially different from the original inviscid design, due to interactions of shocks, boundary layers, and bleed. Good agreement with experimental data was obtained in many aspects. Many of the discrepancies were thought to originate primarily from 3D effects. Therefore, a balance should be struck between expending resources on a high fidelity 20 simulation, and the inherent limitations of 20 analysis. The solutions were fairly insensitive to turbulence models, grids and bleed models. Overall, the k-e turbulence model, and the bleed models based on unchoked bleed hole discharge coefficients or uniform velocity are recommended. 20 Navier-Stokes methods appear to be a useful tool for the design and analysis of supersonic inlets, by providing a higher fidelity simulation of the inlet flowfield than inviscid methods, in a reasonable turnaround time.

P pressure, N/m 2 (psf) p static pressure A numerical study was performed to simulate the critical number flow through a supersonic inlet. This flow field has many R R Gas colGas constant phenomena such as shock waves, strong viscous effects, turRe inlet capture radius, bulent boundary layer development, boundary layer separations and mass flow suction through the walls, (bleed). The 0.4745 m (18.68 in.) TF-30 size computational tools used in this study were two full Navier-0.2116 m ( 8.331 in.) J-85 size