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survey of aerothermodynamics facilities useful for the design of hypersonic vehicles using air-breathing propulsionThis paper surveys the use of aerothermodynamic facilities which have been useful in the study of external flows and propulsion aspects of hypersonic, air-breathing vehicles. While the paper is not a survey of all facilities, it covers the utility of shock tunnels and conventional hypersonic blow-down facilities which have been used for hypersonic air-breather studies. The problems confronting researchers in the field of aerothermodynamics are outlined. Results from the T5 GALCIT tunnel for the shock-on lip problem are outlined. Experiments on combustors and short expansion nozzles using the semi-free jet method have been conducted in large shock tunnels. An example which employed the NASA Ames 16-Inch shock tunnel is outlined, and the philosophy of the test technique is described. Conventional blow-down hypersonic wind tunnels are quite useful in hypersonic air-breathing studies. Results from an expansion ramp experiment, simulating the nozzle on a hypersonic air-breather from the NASA Ames 3.5 Foot Hypersonic wind tunnel are summarized. Similar work on expansion nozzles conducted in the NASA Langley hypersonic wind tunnel complex is cited. Free-jet air-frame propulsion integration and configuration stability experiments conducted at Langley in the hypersonic wind tunnel complex on a small generic model are also summarized.
Document ID
19980018683
Document Type
Conference Paper
Authors
Arnold, James O.
(NASA Ames Research Center Moffett Field, CA United States)
Deiwert, George S.
(NASA Ames Research Center Moffett Field, CA United States)
Date Acquired
August 17, 2013
Publication Date
December 1, 1997
Publication Information
Publication: Future Aerospace Technology in the Service of the Alliance
Volume: 3
Subject Category
Research and Support Facilities (Air)
Distribution Limits
Public
Copyright
Other
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