摘要
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 inverse design method of transonic airfoil and wing is described, in which following modification are made for improving convergence and extending application areas: an artificial viscosity term is added to increase the ability of dealing with the shock; a Riegels type of leading edge correction is taken to remove the singularity at the leading edge of the round-nosed airfoil; a smoothing-relaxation procedure is proposed; all coefficients in the equations are integrated in analytical form. A regularity condition in closed form for the transonic airfoil design is presented. A few design results indicate that this method is effective in the transonic airfoil and wing design.
出处
《航空学报》
EI
CAS
CSCD
北大核心
1992年第10期B463-B468,共6页
Acta Aeronautica et Astronautica Sinica
关键词
跨音速流
翼型
机翼
设计
transonic flow, airfoils, wings, design
