Steady flowfields describing the flow over a 75-deg swept delta wing at M(infinite) = 1.95 and 4.48 x 106 were simulated at alpha = 20 and 30 deg using two computer codes. Comparisons were made between calculations using 1) the laminar and turbulent thin-layer Navier-Stokes equations, and 2) laminar thin-layer and Navier-Stokes equations. -At alpha = 20 deg, each equation set captures the essential structure of the flow and the differences between their results are minor. Numerical results generated by a grid refinement study exhibited only a minor improvement. The Navier-Stokes equations were used to calculate the flow at alpha = 30 deg. A region of reversed flow along the surface near the trailing edge was observed. The vertical extent of this region was much smaller, but the upstream propagation extended much farther than the thin-layer simulation.
Thin-layer full Navier-Stokes simulations over a supersonic delta wing
Vollständige Navier Stokes Simulation für dünne Schichten über einem supersonischen Deltaflügel
AIAA Journal ; 29 , 9 ; 1363-1369
1991
7 Seiten, 16 Bilder, 16 Quellen
Aufsatz (Zeitschrift)
Englisch
High-Resolution Navier-Stokes Computation of Voritcal Flow over a Supersonic Delta Wing (TN)
Online Contents | 1994
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