Supersonic wind tunnel tests of a half-axisymmetric 12⁰-spike inlet to a rocket-based combined-cycle propulsion system /

Bibliographic Details

Main Author:	DeBonis, J. R.
Corporate Author:	NASA Glenn Research Center
Other Authors:	Trefny, C. J.
Format:	Government Document Book
Language:	English
Published:	[Cleveland, Ohio] : Hanover, MD : National Aeronautics and Space Administration, Glenn Research Center ; Available from NASA Center for Aerospace Information, [2001]
Series:	NASA technical memorandum ; 210567.
Subjects:	Air breathing boosters. Hypersonic speed. COMPUTATIONAL FLUID DYNAMICS. Wind tunnel tests. Propulsion. Pressure distribution.
Online Access:	Adobe Acrobat Reader required