由於平面尖角(凸角及凹角)流動問題具奇異性，超音速微小擾動之線性化理論無法計算出其完整之流場解以致失效，本文利用超音速遠場非線性理論，得以適切地處理超音速凹角壓縮流動問題。有關超音速凹角流場之震波位置及楔形體表面壓力係數，本文以超音速遠場非線性理論求得其一階漸近解，並加以推展至穿音速及極音速之範圍，經與完整斜震波理論之精確解及其一階漸近解驗證而獲得滿意之結果，而顯現出超音速遠場理論之實用性與統合性。 Due to the singularity at the corner, the supersonic linearized theoryis invalid for calculating the flow field of supersonic corner flow.By applying the supersonic far field nonlinear theory, the asymptoticsolution from the boundary-value problem of centered compression waveis obtained. The asymptotic results of shock position and the pressurecoefficient on the wedge for supersonic flow is given to the firstorder and the results agree well with the exact solution of obliqueshock wave theory.
