Shock-tunnel combustor testing for hypersonic vehicles
By: Mark Loomis.
Contributors: United States. National Aeronautics and Space Administration.
Series: NASA contractor report -- NASA CR-196836.; MCAT Institute final report -- 94-07.
Publisher: MCAT Institute; National Aeronautics and Space Administration; National Technical Information Service, distributor
Published: 1994
Place of publication: San Jose, Calif; [Washington, DC; Springfield, Va
Language: eng
Format: Microform
Subjects: Wind tunnel tests.; Air breathing engines.; Combustion chambers.; Engine tests.; Hypersonic aircraft.; Hypersonic flow.; Hypersonic inlets.; Hypersonic speed.; Inlet nozzles.; Mach number.; Propulsion system configurations.; Propulsion system performance.; Supersonic combustion ramjet engines.; Two dimensional flow.; Wind tunnel tests.
Other titles: Shock tunnel combustor testing for hypersonic vehicles.
Notes: Distributed to depository libraries in microfiche.

Shipping list no.: 95-0068-M.

Microfiche. [Washington, D.C. : National Aeronautics and Space Administration, 1994] 1 microfiche.