Numerical simulation of three-dimensional supersonic inlet flow fieldsSupersonic inlet flows with mixed external-internal compressions of an axisymmetric inlet model were computed using a combined implicit-explicit (Beam-Warming-Steger/MacCormack) method for solving the three-dimensional unsteady, compressible Navier-Stokes equations in conservation form. Numerical calculations were made of various flows typically found in supersonic inlets such as shock-wave intersections, flow spillage around the cowl lip, shock-wave/boundary-layer interactions, control of shock-induced flow separation by means of boundary layer bleed, internal normal (terminal) shocks, and the effects of flow incidence. Computed results were compared with available wind tunnel data.
Document ID
19870037658
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kawamura, T. (NASA Ames Research Center Moffett Field, CA, United States)
Chyu, W. J. (NASA Ames Research Center Moffett Field, CA, United States)
Bencze, D. P. (NASA Ames Research Center Moffett Field, CA, United States)