[HTML][HTML] 近空间高超声速飞行器气动特性研究的若干关键问题
叶友达， 张涵信， 蒋勤学， 张现峰 - 力学学报, 2018 - lxxb.cstam.org.cn
在30$\sim $70 km 空域机动飞行的高超声速飞行器的优点是可以耦合利用所处空域的空气产生
的升力和高速飞行的离心力进行远距离机动滑翔飞行, 具有重要的实用价值 …
的升力和高速飞行的离心力进行远距离机动滑翔飞行, 具有重要的实用价值 …
[HTML][HTML] Some key problems in the study of aerodynamic characteristics of near-space hypersonic vehicles
Y Youda, Z Hanxin, J Qinxue… - Chinese Journal of …, 2018 - pubs-en.cstam.org.cn
The advantages of the hypersonic vehicle in maneuverable flight in 30$\sim $70 km
airspace are that it can carry out long-distance maneuverable gliding flight by coupling the …
airspace are that it can carry out long-distance maneuverable gliding flight by coupling the …
真实气体效应对升力体舵面局部流动分离的影响
田浩， 叶友达， 蒋勤学， 何先耀 - 空气动力学学报, 2015 - pubs.cstam.org.cn
数值模拟分析了高马赫数低雷诺数条件下激波边界层干扰, 激波与激波相互作用,
流动分离再附等流动现象的特点以及高温真实气体效应的影响. 分别采用量热完全气体 …
流动分离再附等流动现象的特点以及高温真实气体效应的影响. 分别采用量热完全气体 …
[PDF][PDF] The multidisciplinary design optimization of a reentry vehicle using parallel genetic algorithms
The purpose of this paper is to examine the multidisciplinary design optimization (MDO) of a
reentry vehicle. In this paper, optimization of a RV based on, minimization of heat flux …
reentry vehicle. In this paper, optimization of a RV based on, minimization of heat flux …
Stagnation Heat Transfer and Through-Thickness Temperature Profile Calculation at Hypersonic Speeds
D Mazarakos, D Sikoutris, E Panagiotopoulos… - 14th AIAA/AHI Space …, 2006 - arc.aiaa.org
Subscripts 1= upstream properties (region 1) 2= downstream properties (region 2) t2=
stagnation region properties S= stagnation point w= vehicle's wall stored, S= stored …
stagnation region properties S= stagnation point w= vehicle's wall stored, S= stored …