跨声速风洞洞壁干扰实验研究  

THE EXPERIMENTAL RESEARCH OF WALL INTERFERENCE IN TRANSONIC WIND TUNNEL

作　　者：荣柏森[1] 

机构地区：[1]南京航空航天大学

出　　处：《气动实验与测量控制》1994年第2期28-34,共7页

摘　　要：本文研究洞壁干扰对ＰＴ８－９９全机模型气动力的影响。结果表明，它对机翼压力分布的影响主要在机翼前缘压力变化大区域和后部激波区，且随来流马赫数增加而增加。它对Ｃｙ的影响相对较小，当模型堵塞度为０．６％时，可认为洞壁对Ｃｙ的影响可忽略不计。洞壁干扰对模型俯仰力矩影响较大，即使模型堵塞度为０．６％，还存在着洞壁对Ｍｚ的干扰。The effect of wall interference on the aerodynamical characteristics of Model PT8-99 is inyestigated in this paper.The results show,its influence on the pressure distribution concentrates mainly in the regions with large pressure variation and shock wave both separately on theleading edge and rear part of wing, it increases with free flow Machnumber. The influence of wall interference on Cy is smaller, as the blockage of model is 0.6%, its effect on Cy is very small.The influence of wallinterference on Mz. is larger,eyen the blockage of model is only 0.6%, itsinfluence on Mz still exists.

关 键 词：跨声速流动 洞壁干扰 堵塞度 风洞 

分 类 号：V211.74[航空宇航科学与技术—航空宇航推进理论与工程]