Numerical Study of the Viscous HypersonicFlow over a Blunt Delta Wing

摘要

A previously developed two-dimensional Navier— Stokes solver is extended to three dimen-sions. The hypersonic steady flow of an perfect gas (with a constant adiabatic index) over a delta wingwith a spherical nose and a cylindrical leading edge is computed as an example. The characteristic fea-tures of the flow are analyzed. Pressure, heat flux, and friction coefficient distributions are computedin the shock layer and on the wing surface. The results are compared with available numerical andexperimental data.