高超声速层流干扰流场研究  

Investigation of Laminar interactive flowfield in hypersonic flow

作　　者：李素循[1] 倪招勇[1] 

机构地区：[1]北京空气动力研究所,北京100074

出　　处：《宇航学报》2003年第6期547-551,573,共6页Journal of Astronautics

基　　金：国防科技预研基金(00J13;2;41177103)

摘　　要：文章研究了高超声速来流绕三维凸起物的层流干扰流场特征。研究工作在M=8轻活塞式炮风洞内完成,通过可改变楔角的模型试验给出纹影照片与特征位置的表面压力分布,分析了楔角变化引起的流动分离范围的变化、激波系的生成与演变以及压力分布及压力峰值改变规律。The interactive flow of the laminar boundary induced by three dimensional obstacle was studied at hypersonic speed.The experiments were carried out in the gun tunnel with light piston (M=8).The test model consisted of two parts,the basic flat plate and the 3D wedge;the wedge angle could be changed from 10° to 40°.This model looked like a component as a control wing on the vehicle surface or a ramp in the scramjet.Since the loads on the surface including pressure and heat flux were very important for engineering design problem.In present paper for four typical cases the schlieren photos and static pressure distributions were shown.The results indicated that the effect of different wedge angles on the flow separated range and shock waves structure evolution as well as pressure distributions,several new phenomena on 3D interactive flow had been provided.

关 键 词：高超声速流 激波/边界层干扰 分离流 压力测量 

分 类 号：V411[航空宇航科学与技术—航空宇航推进理论与工程]