NASA has contracted with the Central Institute of Aviation Motors CIAM to perform a flight test and ground test and provide a scramjet engine for ground test in the United States. The objective of this contract is to obtain ground to flight correlation for a supersonic combustion ramjet (scramjet) engine operating point at a Mach number of 6.5. This paper presents results from a flow path performance and thermal evaluation performed on the design proposed by the CIAM. This study shows that the engine will perform in the scramjet mode for stoichiometric operation at a flight Mach number of 6.5. Thermal assessment of the structure indicates that the combustor cooling liner will provide adequate cooling for a Mach number of 6.5 test condition and that optional material proposed by CIAM for the cowl leading-edge design are required to allow operation with or without a type IV shock-shock interaction.
Comparative Flow Path Analysis and Design Assessment of an Axisymetric Hydrogen Fueled Scramjet Flight Test Engine at a Mach Number of 6.5
2004
20 pages
Report
Keine Angabe
Englisch
Aircraft , Test Facilities & Equipment , Jet & Gas Turbine Engines , Flight tests , Supersonic combustion ramjet engines , Ground tests , Thermal evaluation , Analytical methods , Thermal predictions , Mach numbers , Design proposal , Hypersonic flight , Engine tests , Central Institute of Aviation Motors(CIAM) , Flow path performance , Hypersonic speed
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