Measurement and imaging of supersonic combustion in a model scramjet engine

被引：6
|
作者：
O'Byrne, S [1 ]
Doolan, M [1 ]
Olsen, SR [1 ]
Houwing, AFP [1 ]
机构：
[1] Australian Natl Univ, Fac Sci, Dept Phys, Aerophys & Laser Based Diagnost Res Labs, Canberra, ACT 0200, Australia
来源：
SHOCK WAVES | 1999年 / 9卷 / 04期
关键词：
supersonic combustion; shock tunnel; shadowgraph; flow imaging; numerical simulation;
D O I：
10.1007/s001930050159
中图分类号：
O3 [力学];
学科分类号：
08 ; 0801 ;
摘要：
Results of tests performed in a free-piston shock tunnel on a model scramjet engine are presented. Two conditions which differed in Mach number were tested. Flow at the lower Mach number condition was achieved using a variable-angle diffuser. Shadowgraph images and floor static pressure measurements were obtained, the latter used as the basis of a finite-difference calculation of flow properties in the scramjet.
引用
收藏
页码：221 / 226
页数：6
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