本文主要引用漸近展開法，針對氣體動力學中之超音速、穿音速與極音速之勢流微擾理論加以整合探討，並以凹角流動邊界值問題為例，求得其流場之漸近解，並與對應之凹角斜震波理論之精確解加以驗證。由於楔形體之凹角為奇異點，超音速微小擾動之線性化理論無法計算其完整之流場解以致失效，吾人利用變形座標法重新建立超音速非線性漸近理論得以正確處理凹角流動問題。有關凹角流場之震波位置及楔形體表面壓力係數，本文以勢流微擾理論求得之超音速、穿音速與極音速之一階漸近解，經與斜震波理論之精確解驗證而獲得滿意之結果。 The essential point of view in this paper is to re-examine the small perturbation theory of supersonic, transonic and hypersonic flow. The asymptotic solutions of boundary value problems of centered compression wave for supersonic, transonic and hypersonic nonlinear small disturbance equations are exhibited. The asymptotic solutions of centered compression wave are verified from the exact solution of the oblique shock wave theory respectively.
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一九九九中華民國「航太學會/燃燒學會/民航學會」航太學術聯合會議論文集=Proceedings of the 1999 AASRC/ CIROC/ CSCA Aerospace Joint Conference，頁41282
