烧蚀外形气动加热及压力分布实验研究  

Experimental Study of Aerodynamic Heating and Pressure Distribution on Indented Nosetip Models

作　　者：苟光贤 林文冰 

机构地区：[1]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》1992年第3期293-299,共7页Acta Aerodynamica Sinica

摘　　要：本文叙述了在中国空气动力研究与发展中心激波风洞中进行的烧蚀外形气动热环境试验研究。实验所用的自由流状态为:M_∞=7.90～12.40,Re_∞/m=1.3×10~7～4.3×10~7。共研究了7种不同的外形。这些外形都是先进的端头再入过程中可能出现的典型形状。研究的重点是凹陷外形。测量了模型表面的热流和压力分布,并进行了纹影流场显示。研究了马赫数及雷诺数的影响,还对粗糙度的影响进行了实验。The experimental study is given of the aerothermal circumstance on ablated nosetip models in the shock tunnels of CARDC. The freestream conditions at which the models were studied are M∞= 7.90~12.40 and Re∞ = 1.30 × 107~4.30 ×107. Seven kinds of models of various shapes were used. The models are typical configurations formed possi-bily in the process of reentry of the advanced nosetip. The emphasis is put on the indented models. The distributions of heat flux and pressure on the models were measured. Some schlieren photographs were also given. The effects of Mach numbers and Reynolds numbers and the influence of the roughness on heat flux augmentation were studied.

关 键 词：高超音速流动 热传导 烧蚀 

分 类 号：V211.1[航空宇航科学与技术—航空宇航推进理论与工程]