Supersonic wind tunnel tests of a half-axisymmetric 12°-spike inlet to a rocket-based combined-cycle propulsion system /

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Bibliographic Details
Author / Creator:	DeBonis, James R., author.
Imprint:	Cleveland, Ohio : National Aeronautics and Space Administration, Glenn Research Center, February 2001.
Description:	1 online resource (18 pages) : illustrations.
Language:	English
Series:	NASA/TM ; 2001-210567 NASA technical memorandum ; 2001-210567.
Format:	E-Resource U.S. Federal Government Document Book
URL for this record:	http://pi.lib.uchicago.edu/1001/cat/bib/11554050

Hidden Bibliographic Details
Varying Form of Title:	Supersonic wind tunnel tests of a half-axisymmetric 12 degree spike inlet to a rocket-based combined-cycle propulsion system
Other authors / contributors:	Trefny, Charles J., author. NASA Glenn Research Center, issuing body.
Notes:	"February 2001." "Prepared for the 37th Combustion Subcommittee, 25th Airbreathing Propulsion Subcommittee, and 19th Propulsion Systems Hazards Subcommittee Joint Meeting sponsored by the Joint Army-Navy-Air Force Interagency Propulsion Committee, Monterey, California, November 13-17, 2000." "Performing organization: National Aeronautics and Space Administration, John H. Glenn Research Center at Lewis Field"--Report documentation page. Includes bibliographical references (page 5). Technical memorandum. Sponsored by the National Aeronautics and Space Administration WU-523-61-33-00 E-12533 Description based on online resource; title from PDF title page (NASA, viewed Nov. 13, 2017).
Other form:	Print version: Supersonic Wind Tunnel Tests of a Half-Axisymmetric 12 Deg-Spike Inlet to a Rocket-Based Combined-Cyc Microfiche version: DeBonis, James R. Supersonic wind tunnel tests of a half-axisymmetric 12°-spike inlet to a rocket-based combined-cycle propulsion system
GPO item no.:	0830-D (online)
Govt.docs classification:	NAS 1.15:210567

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