As examples, an quasi-one-dimensional nozzle flow with shock and the subsonic and transonic flow about NACA-0012 and NACA64A-10 airfoils are calculated. The results are compared with the experimental data and the other computed results.
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- 文中分別對一維管流,二維繞NACA-0012和NACA64A-10翼型在亞聲速和超聲速來(lái)流的跨聲速流場(chǎng)進(jìn)行了計算,并將所得結果與有關(guān)實(shí)驗和計算結果進(jìn)行了比較,均符合良好。
