An analysis is presented for calculating steady (or unsteady) three-dimensional supersonic fighter intake flowfields. This algorithm can compute the flowfield about forebody, inlet, and diffuser configurations at zero or nonzero incidence. The algorithm can solve either the Euler momentum equations for inviscid flow, the thin-shear-layer Navier-Stokes equations for viscous flow, or the full Navier-Stokes equations for viscous flow. The flowfield is determined on a body-fitted numerically-generated computational grid. A fully-implicit alternating-direction-implicit algorithm is employed for solution of the finite-difference equations. Viscous flow results are presented to illustrate application of the analysis for cases at supersonic free-stream speeds.
Navier-Stokes simulations of supersonic fighter intake flowfields
Navier Stokes Simulation des Einlaufstroemungsfeldes von Ueberschallkampfflugzeugen
AIAA-Papers ; Jul ; 1-16
1987
16 Seiten, 7 Bilder, 21 Quellen
Conference paper
English