Further Development of AIDC High Order Panel Method

AIDC全機高階小板法

陳秉智(P.C. Chen) ； 林鴻佳(H. C. Lin) ； 楊禮彰(L. J. Yang)

《中國航空太空學會學刊》 26卷1期 (1994/03) Pp. 33-41

https://doi.org/10.6124/TAASRC.199403_26(1).04

摘要

本文的數值方法爲一高階(High Order)且能計算全機復雜外形之超音速氣動力小板法，在每塊小板上放置線性分佈偶極(Linear Doublet)及常數分佈源極(Constant Source)來模擬流場特性，同時對於邊界條件的設定係數採用平均積分的型式(Integral Averaged Boundary condition)，確保小板機何外形和偶極分佈之連續性，如此一來可以消除不必要的干擾內波(Internal Wave)，維持超音速流場計算的精確性與穩定性。數值結果顯示，本文提出之方法和PANAIR有相同的準確度，但是在計算上則更有效率。

關鍵字

線性分佈偶極 ； 常數分佈源極 ； 小板法

並列摘要

The present method is a computer program for predicting supersonic linear potential flow about arbitrary configuration. It uses constant source and linear doublet strength distributions. The so-called ＜||＞integral averaged boundary condition＜||＞ is applied on both Neumann and Dirichlet forms. It is found out that, for computational efficiency, the present method uses the lowest singularity variation allowed for supersonic flow, but yields accurate and stable results compared to other more expensive methods such as PANAIR.

並列關鍵字

Linear Doublet ； Constant Source ； Panel Method