航空学报 > 1988, Vol. 9 Issue (11): 499-508

无激波机翼的设计方法

朱自强   

  1. 北京航空航天大学
  • 收稿日期:1987-11-07 修回日期:1900-01-01 出版日期:1988-11-25 发布日期:1988-11-25

A METHOD FOR SHOCK-FREE WING DESIGN

Zhu Ziqiang   

  1. Beijing University of Aeronautics and Astronautics
  • Received:1987-11-07 Revised:1900-01-01 Online:1988-11-25 Published:1988-11-25

摘要: 本文介绍了用虚拟气体概念进行无激波机翼设计的方法,叙述了虚拟气体方法的基本思路;给出了几种虚拟气体规律,以小扰动方程为例具体说明了在超音区内的推进计算过程。分别讨论了二维和三维情况,设计和非设计状态时的效益。最后介绍了近无激波机翼修型的工程设计方法。

Abstract: A method for shock-free wing design using "fictitious gas"concept is comprehensively introduced in the paper.The main points of this method are briefly described. Several fictitious gas laws are presented. A spece-matching procedure adopted in supersonic flow region is concretely explained.The gain in 2-D or 3-D design conditions and off-design conditions is also discussed . Finally, an engineering approach for nearly shock-free wing design is introduced.