高超声速边界层的转捩问题  

A study of the transition prediction of hypersonic boundary layer on plane and wedge flow

作　　者：曹伟[1,2] 

机构地区：[1]天津大学力学系,天津300072 [2]南开大学天津大学刘徽应用数学研究中心,天津300072

出　　处：《空气动力学学报》2009年第5期516-523,共8页Acta Aerodynamica Sinica

基　　金：国家自然科学基金重大研究计划资助项目(90716007);全国优秀博士学位论文作者专项基金资助项目(200328)

摘　　要：取40km高空处的气体参数,对来流马赫数为8、10和12等三种不同情况的平板边界层和楔角为20°的楔型体边界层,做了转捩发生位置的预测。所用方法为改进的eN方法。结果发现,壁面条件对是第一还是第二模态波决定转捩位置有很大关系。如对于传统的eN方法,如果取N为10作为转捩判断标准,对马赫数为12的楔体边界层,等温壁条件下由第二模态波决定的转捩位置距前缘13m左右,而平板边界层中两模态波所决定的转捩位置距前缘均超过50m。而采用改进的eN方法,平板边界层中两模态波所决定的转捩位置距前缘均超过10m,而对马赫数为12的楔体边界层,两模态波所决定的转捩位置距前缘均出现小于5m的情况。In this paper, the position of transition was predicted of hypersonic boundary layer on the plane and wedge with 20 degree angle. The flow parameters were taken as those corresponding to the condition at a height of 40km and the Math numbers of oncoming flow were 8, 10, 12 respectively. The improved eN method was used to give transition position. It is found that the wall condition affect whether the first or the second mode wave plays a dominant role in transition. According to the results of the traditional en method, if N was taken 10 as the crisis for judging if the transition occurred, we found that in the wedge boundary layer with oncoming flow of Mach number 12, the second mode wave determined the transition if the wall was isothermal one, and the position was 13m apart from the leading edge. In addition, the transition position exceeded 50m and was decided by two kinds of mode wave in the plane boundary layer. Whereas from the result obtained from the improved en method, in the plane boundary layer, the transition position was also decided by two kinds of mode wave but the position exceeded only 10m. and in wedge boundary layer flow with Mach 12, the transition position was less than 5m apart from the leading edge.

关 键 词：高超声速 边界层 转捩 

分 类 号：O357.4[理学—流体力学]