A review of fundamental research in combustion stabilization for hypersonic airbreathing
propulsion is presented. Combustion in high-speed airbreathing propulsion systems …

Plasma assisted combustion is a promising technology to improve engine performance,
increase lean burn flame stability, reduce emissions, and enhance low temperature fuel …

This paper presents an overview and analysis of the various aspects of hypersonic ground
testing. For this, first the simulation requirements according to the different flow regimes of …

This study reports the first experiments of a large-scale hydrogen-fueled oblique detonation
engine model conducted in a hypersonic wind tunnel. The stabilization characteristic of …

In this study, the performances of a Mach 9 oblique detonation engine fueled by hydrogen
are numerically investigated by solving the multi-species reactive Reynolds-averaged …

An ethylene-fueled scramjet operating at Mach 10 was experimentally tested in the JF-24
shock tunnel and modeled using improved delayed detached eddy simulation based on up …

针对高超声速飞行伴随的热化学反应流动, 本文回顾了郭永怀先生的科研理念和学科布局,
综述了他亲手成立的高温气动团队在高超声速飞行风洞实验模拟理论与方法方面的研究进展 …

随着飞行马赫数的不断提高, 空气的高温气体效应越来越明显, 对高超声速飞行器的气动力/热
特性产生重要影响. 高温气体效应对气动力/热的影响机理复杂, 影响参数众多 …

Hypersonic and high-enthalpy wind tunnels and their measurement techniques are the
cornerstone of the hypersonic flight era that is a dream for human beings to fly faster, higher …

针对高Mach 数超燃冲压发动机实验能力空缺问题, 基于航天十一院新建的FD-21 高能脉冲风洞,
进行了Ma= 8 超燃飞行条件的模拟能力设计与调试, 获得了总焓2.9 MJ/kg, 总压11.01 MPa …