摘要
作为我国航天飞机研究的一个开端，本文以美国ＮＡＳＡ高超音速研究发动机ＨＲＥ的进气道几何为模型，进行了飞行马赫数为６时的进气道各部分的气动和气动热计算，并在此基础上提出了以氢燃料作冷却剂的主动冷却结构，进行了冷却计算，证明提出的冷却结构所需要的氢用量是合理的。
As an initiation for the study of aerospace aircraft, in this article aerothermodynamic prediction of hypersonic inlet was presented. Based on the predicted distribution of heat flux the enhanced cooling method for the inlet casing, central cylinder and its front cone were suggested. Prediction results showed that the required quantity of hydrogen for the active cooling of stainless steel inlet will be below 0.4 kg/s.
出处
《工程热物理学报》
EI
CAS
CSCD
北大核心
1994年第2期174-178,共5页
Journal of Engineering Thermophysics
关键词
进气道
气动热
冷却
高超音速
inlet, aerodynamic heating, enhanced cooling.
