Supersonic wind tunnel tests of a half-axisymmetric 12⁰-spike inlet to a rocket-based combined-cycle propulsion system
By: J.R. DeBonis and C.J. Trefny.
Contributors: Trefny, C. J.; NASA Glenn Research Center.
Series: [NASA technical memorandum] -- NASA/TM-2001-210567.; NASA technical memorandum -- 210567.
Publisher: National Aeronautics and Space Administration, Glenn Research Center; Available from NASA Center for Aerospace Information
Published: 2001
Place of publication: [Cleveland, Ohio]; Hanover, MD
Language: eng
Format: Microform
Subjects: Air breathing boosters.; Hypersonic speed.; Computational fluid dynamics.; Wind tunnel tests.; Propulsion.; Pressure distribution.
Notes: Shipping list no.: 2002-0157-M.

Also available via Internet from the NASA web site. Address as of 10/10/02: http://gltrs.grc.nasa.gov/reports/2001/TM-2001-210567.pdf ; current access is available via PURL.

Microfiche. [Washington, D.C. : National Aeronautics and Space Administration, 2001?] 1 microfiche.