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为研究初场对计算结果的影响,本文从二元定常跨音速小扰动方程出发,用混合有限差分松弛迭代法对NACA 0012翼型作了计算。计算结果表明,在来流为超临界的情况下,用非守恒差允格式捕捉激波时,以低熵值的初场(零值、小于计算攻角或马赫数的计算结果)进行迭代计算,就能较好地获得正确的收敛解,否则就可能得出错误的收敛解。在亚临界情况下,流场不出现激波,所以计算不受初场选取的影响,即收敛解是唯一的。
In order to study the effect of initial stage on the calculation results, this paper starts with the small perturbation equation of transonic tardiness and computes the NACA 0012 airfoil by using the hybrid finite difference relaxation relaxation method. The results show that when the shock wave is captured by the non-conservative finite difference scheme, the initial field with low entropy value (zero value, less than the calculated angle of attack or Mach number) is iteratively calculated when the incoming flow is supercritical , You can get the correct convergence solution better, or you may get the wrong convergence solution. In the subcritical case, the shock wave does not appear in the flow field, so the calculation is not affected by the initial selection, that is, the convergence solution is unique.