Numerical Solution for Three-Dimensional Inviscid Supersonic Flow

An exact finite-difference solution is developed for steady, inviscid, supersonic flow over smooth threedimensional bodies. The method is applied to a blunt delta wing having straight leading edges and an elliptical cross section. Results are presented for angles of attack up to 30° in both perfect gas and equilibrium air at typical freestream conditions for space shuttle orbiter re-entry. The effects of angle of attack on shock layer structure, on surface pressure distributions, and on surface streamline patterns are investigated. Marked variations are found in the structure of the entropy layer over different portions of the surface; the implications for boundary-layer heat-transfer analyses are discussed.