飛彈側向噴流之氣動力性能分析

The Aerodynamic Characteristics of the Supersonic Missile with Side Jet

楊世昌(S.C. Yang) ； 李鴻才(H. T. Lee)

《中國航空太空學會學刊》 35卷2期 (2003/06) Pp. 169-174

https://doi.org/10.6124/TAASRC.200306_35(2).07

摘要

本文的目的，是希望能藉由數值方法來模擬不同成份之側向噴流對超音速飛彈流場的平涉特性與現象，故採用的統御方程式爲不含化學反應多成份氣體混合之Navier-Stokes方程式。在空間離敵方面，黏性項採用中央插分法，而非黏性項則採用適量向輩分離模式(FVS)與適量差分分離模式(FDS)所組合而成之調節性混合法。本調節性混合法擷取YFVS與FDS的優點，可以提高計算的精度與強穩性：又爲了加速求得穩態解，本文在時間差分上採用LU-SGS隱式解法。本數值方法經過測試及驗證後，證明其運用在超音速飛彈倒向噴流流場之數值模擬具有精確及強穩之特性。

關鍵字

側向噴流 ； 超音速流 ； FVS ； FDS

並列摘要

In this paper, we adopt a numerical method to simulate the aerodynamic characteristics of the supersonic missile with side jet. An efficient method for solving the full Navier-Stokes equations with multi-species mixture gas is developed. In order to solve the steady-state solutions of the three-dimensional compressible Navier-Stokes equations in generalized coordinate system, an implicit scheme is adopted to combine several ingredients: lower-upper symmetric Gauss-Seidel relaxation (LU-SGS), adaptive hybrid scheme of flux vector splitting and flux difference splitting spatial operators for inviscid fluxes and central differencing for viscous fluxes. This scheme is used to simulate the supersonic missile with side jet. Its solutions are found to agree with experimental data very well.

並列關鍵字

Side jet ； Supersonic flow ； FVS ； FDS