Measurement and imaging of supersonic combustion in a model scramjet engine

S. O'Byrne; M. Doolan; S. R. Olsen; A. F.P. Houwing

doi:10.1007/s001930050159

Measurement and imaging of supersonic combustion in a model scramjet engine

S. O'Byrne, M. Doolan, S. R. Olsen, A. F.P. Houwing^*

^*Corresponding author for this work

Research output: Contribution to journal › Article › peer-review

12 Citations (Scopus)

Abstract

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.

Original language	English
Pages (from-to)	221-226
Number of pages	6
Journal	Shock Waves
Volume	9
Issue number	4
DOIs	https://doi.org/10.1007/s001930050159
Publication status	Published - 1999

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10.1007/s001930050159

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title = "Measurement and imaging of supersonic combustion in a model scramjet engine",

abstract = "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.",

keywords = "Flow imaging, Numerical simulation, Shadowgraph, Shock tunnel, Supersonic combustion",

author = "S. O'Byrne and M. Doolan and Olsen, \{S. R.\} and Houwing, \{A. F.P.\}",

year = "1999",

doi = "10.1007/s001930050159",

language = "English",

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pages = "221--226",

journal = "Shock Waves",

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T1 - Measurement and imaging of supersonic combustion in a model scramjet engine

AU - O'Byrne, S.

AU - Doolan, M.

AU - Olsen, S. R.

AU - Houwing, A. F.P.

PY - 1999

Y1 - 1999

N2 - 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.

AB - 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.

KW - Flow imaging

KW - Numerical simulation

KW - Shadowgraph

KW - Shock tunnel

KW - Supersonic combustion

UR - https://www.scopus.com/pages/publications/0033434476

U2 - 10.1007/s001930050159

DO - 10.1007/s001930050159

M3 - Article

SN - 0938-1287

VL - 9

SP - 221

EP - 226

JO - Shock Waves

JF - Shock Waves

IS - 4

ER -

Measurement and imaging of supersonic combustion in a model scramjet engine

Abstract

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