Facility requirements for hypersonic propulsion system testing are reviewed. The significant contributions of some previous studies are put in perspective with on-going work, and suggestions for additional effort are included. The capabilities and limitations of selected hypersonic testing facilities are briefly reviewed. The specific advantages and limitations of the shock tunnel for hypersonic propulsion testing are discussed, and areas are identified where shock-tunnel research can supplement other ground tests and flight experiments in the development of air-breathing propulsion. Other papers in the session will describe some of the other facilities in detail so the discussion in the paper will be confined to a more detailed discussion intended to respond to many of the perceived limitations associated with the short-duration approach typical of the reflected-shock tunnel. Sample calculations have been performed to examine real-gas effects on the simulation of flows about hypersonic vehicles. Shock-tunnel testing of both scramjet combustor and exhaust nozzle configurations at conditions corresponding to flight at Mach number of 10-12 at altitudes of 100000 ft. are considered. It is demonstrated that nozzle expansion of air in these cases remain in vibrational and chemical equilibrium well into the supersonic region. At the point where finite-rate computations are required, the expanding flow has already returned to the essentially undissociated state corresponding to low temperature air.
Facility requirements for hypersonic propulsion system testing
Anforderungen an eine Anlage zur Pruefung von Hyperschallgeschwindigkeitsantrieben
AIAA-Papers ; Jan ; 1-15
1989
15 Seiten, 5 Bilder, 1 Tabelle, 53 Quellen
Aufsatz (Konferenz)
Englisch