航空学报 > 1992, Vol. 13 Issue (10): 463-468

跨音速翼型和机翼的反设计计算方法

朱自强, 夏智勋, 吴礼义   

  1. 北京航空航天大学流体力学研究所 北京 100083
  • 收稿日期:1991-10-22 修回日期:1992-03-28 出版日期:1992-10-25 发布日期:1992-10-25

AN INVERSE DESIGN METHOD OF TRANSONIC AIRFOIL AND WING

Zhu Zi-qiang, Xia Zhi-xun, Wu Li-yi   

  1. Institute of Fluid Mechanics, Beijing University of Aeronautics and Astronautics,Beijing, 100083
  • Received:1991-10-22 Revised:1992-03-28 Online:1992-10-25 Published:1992-10-25

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。

关键词: 跨音速流, 翼型, 机翼, 设计

Abstract: 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.

Key words: transonic flow, airfoils, wings, design