同時將超音速凹角壓縮流動邊界值問題轉換至極音速流場，其所求得之結果與直接由極音速全場邊界值問題所求得之結果完全相同，換言之，超音速凹角壓縮流動全場解統合了極音速全場解。" "Due to the singularity at the corner, a supersonic or hypersonic flow past a corner is essentially a nonlinear problem. The governing equations for these flows are supersonic and hypersonic nonl inear small disturbance potential equations. The similarity solutions of these boundary value problems are derived in this work and the results agree well with the asymptotic solution from the oblique shock wave theory.
The governing equations for the supersonic and hypersonic flows are completely different. It is worth mentioning that the asymptotic solution of hypersonic flow past a corner can be approached by the asymptotic solution of supersonic flow using the expansion of free Mach number in terms of hypersonic simi lari ty parameters. The results of this study show that the supersonic nonlinear solution constructed for the corner flow is correct and the solutions for corner floware unified for supersonic and hypersonic small disturbance theories."