本文利用數值方法模擬分析彈體於高攻角之流場，數值方法是以上風的有限體積法來求解穩態的威爾-史托客方程式(Navier-Stokes equations)，並採用三階的上風有限體積法計算對流項，採用中央差分有限體積法計算黏滯項，進而利用交錯方向隱式法DDADI對時間積分，並加入隱式殘值平滑性（implicit residual smoothing）加速穩態計算的收斂性。
本數值研究，是以Tangent-ogive彈體為物理模型。主要是針對流體在相同雷諾數，不同攻角下，探討彈體之氣動力係數，並計算CP，Cn值，最後結合實驗數據與數值模擬結果分析得知，當彈體以較高攻角飛行時，分離現象非常明顯，且增加彈體正向力。

A numerical method is developed to study the flow field over a missile at high angle of attack. The method solves the compressible Navier-Stokes equations. It uses a third-order upwind finite-volume scheme for discretizing the convective terms and a second-order central finite-volume scheme for discretizing the viscous terms. A DDADI time integration coupling with an implicit residual smoothing is used for achieving fast convergence.
A Flow over a tangent ogive-forebody is tested to verify the numerical method. At same Reynolds number，the flows past a missile under different higher angles of attack are simulate to investigate the aerodynamic performance，such that Cp and Cn. Finally，form the numerical solutions and experiment data, it show that higher incidence flow produces the large regions of flow separation and increases the normal force.

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