Euler and Navier-Stokes leeside flows over supersonic delta wings

Numerical simulations of several distinctly different types of leeside flowfields over higly swept, sharp, leading-edge delta wings in supersonic flow were obtained using Euler and Navier-Stokes solvers. The Euler code was seen to be adequate for predicting primary flow structures (leading-edge vortex and crossflow shock), whereas the Navier-Stokes code was capable of predicting primary and secondary flow structures (i.e., secondary vortex and shock-induced separation). A comparison of laminar and turbulent Navier-Stokes solutions for leading-edge separated flows for which the boundary-layer state was known indicated that the turbulent boundary-layer model is more accurate in predicting the effect of the boundary layer on the flowfield. Also, for several cases, the Navier-Stokes code indicated detailed flow structures not observed in the qualitative experimental data available.

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