亚超音速机翼最佳弯扭综合设计计算方法

AN INTEGRATED DESIGN COMPUTATIONAL METHOD FOR THE WING OPTIMIZATION CAMBER AND TWIST AT SUBSONIC AND SUPERSONIC FLOW

本文介绍一种亚超音速机翼最佳弯扭综合设计的计算方法,它应用了有限基本解方法。分别在亚超音速各选取一个设计点(M数和C_L),进行机翼弯扭设计,其目的是减小与升力相关的阻力。在此基础上,顾及亚音速和超音速这两个设计点的气动力特性,还要兼顾到飞机其它性能和结构上实现的可能性,进行机翼的综合设计。本文分别给出了亚音速最佳弯扭设计,超音速最佳弯扭设计和综合设计的计算结果。经过分析表明,计算结果是合理的。

An integrated design computational method for the wing optimization camber and twist at subsonic and supersonic flow has been presented in this paper. This method is based on an element solution methed. The wing design has been carried out in the choosing design points (CM and CL) at subsonic and supersonic flow. According to these results, the integrated design has been proceeded considering the aerodynamic characteristics at the design points for subsonic and supe-rsonic flow, meanwhile, matching for the other performance of the aircraft and the possibility on the structure of aircraft. Some results for the wing optimization camber and twist design at subsonic and sup-ersonic flow as well as those of the integrated design have been given in this paper. Analysing this results, we find that they are quite reaso-nable.