跨声速旋成体头部脱体激波的研究  

An Investigation on Detached Shock Waves Ahead of Bodies of Revolution at Transonic Speeds

作　　者：程克明[1] 黄奕裔 

机构地区：[1]南京航空学院空气动力学系

出　　处：《南京航空学院学报》1990年第3期1-6,共6页

基　　金：国家自然科学基金

摘　　要：本文在实验结果基础上,给出了一种计算锥—柱—船尾、拱—柱—船尾和圆球这三类旋成体脱体激波的工程方法。作为一个比较经典的方法,文[1]给出的方法已广泛用来计算物体低超声速飞行时的头部脱体激波。我们知道,理论上能检验脱体波计算合理与否的必要条件是圆锥激波脱体条件。考察文[1]方法后发现,该方法理论上不满足激波脱体条件;究其原因是由于物面肩部发出的声速线处理得较实际过于倾斜。实验结果表明,在M_∞→1时,声速线在物体横向相当一段范围内近乎垂直来流方向。据此本文对文[1]方法做了相应修正。修正过的方法既能满足激波脱体条件,又能与实际吻合较好;而且本方法适用范围较广。Based on the experimental results, an engineering method for calculating detached shock waves ahead of three kinds of bodies, cone-cylinder-boattail, ogive-cylinder-boattail and sphere, is presented in this paper. The method, presented in Ref.[1], as a relatively classical one, has beem used widely for predicting the detached shock wave ahead of a body at lower supersonic speeds. It is well-known that the detachment condition for conical shock wave is a necessary condition on which whether a prediction is valid or not can be examined theoretically. Examination of the method developed in Ref.[1] proves that the method does not theoretically satisfy the shock wave detachment condition, for which the reason is that in dealing with the sonic line, Ref.[1] treated the sonic line emitted at the shoulder on a body as a more inclined one than that in practical case. The experimental results show that the sonic line, particularly at M∞→1, is almost perpendicular to the free-stream direction in a rather long lateral distance from the body surface. Accordingly, a corresponding correction is made in this paper. The corrected method satisfies both the theoretical detachment condition and the practical cases simultaneously. And the method is applicable in a relatively wide range.

关 键 词：旋成本 跨声速 脱体激波 头部 

分 类 号：V211.42[航空宇航科学与技术—航空宇航推进理论与工程]