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

11 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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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.",

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AU - Doolan, M.

AU - Olsen, S. R.

AU - Houwing, A. F.P.

PY - 1999

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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

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DO - 10.1007/s001930050159

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VL - 9

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JO - Shock Waves

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Measurement and imaging of supersonic combustion in a model scramjet engine

Abstract

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