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给出一种跨音速翼型和机翼的反设计计算方法。对所应用的积分方程反方法引入人工粘性项;采用Riegels因子法消除前缘奇性;对强激波问题采用光滑-松弛过程;并将方程中的系数积分成解析形式;对二维翼型反设计计算还提出了一种封闭形式的正则化条件。算例结果表明,该方法对跨音速翼型和机翼设计是一种有效的工具。
An anti-design method of transonic airfoil and wing is given. Artificial viscous terms are introduced to the inverse method of the integral equation applied. Ricketts factor method is used to eliminate the singularity of the leading edge. Smooth-relaxation process is applied to the strong shock problem. The coefficients in the equation are integrated into the analytic form. Anti-design calculations also propose a closed form of regularization conditions. The results show that this method is an effective tool for the design of transonic airfoils and wings.