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Mach 5 to 7 RBCC Propulsion System Testing at NASA-LeRC HTFA series of Mach 5 to 7 freejet tests of a Rocket Based Combined Cycle (RBCC) engine were cnducted at the NASA Lewis Research Center (LERC) Hypersonic Tunnel Facility (HTF). This paper describes the configuration and operation of the HTF and the RBCC engine during these tests. A number of facility support systems are described which were added or modified to enhance the HTF test capability for conducting this experiment. The unfueled aerodynamic perfor- mance of the RBCC engine flowpath is also presented and compared to sub-scale test results previously obtained in the NASA LERC I x I Supersonic Wind Tunnel (SWT) and to Computational Fluid Dynamic (CFD) analysis results. This test program demonstrated a successful configuration of the HTF for facility starting and operation with a generic RBCC type engine and an increased range of facility operating conditions. The ability of sub-scale testing and CFD analysis to predict flowpath performance was also shown. The HTF is a freejet, blowdown propulsion test facility that can simulate up to Mach 7 flight conditions with true air composition. Mach 5, 6, and 7 facility nozzles are available, each with an exit diameter of 42 in. This combination of clean air, large scale, and Mach 7 capabilities is unique to the HTF. This RBCC engine study is the first engine test program conducted at the HTF since 1974.
Document ID
19970011572
Document Type
Conference Paper
Authors
Perkins, H. Douglas (National Aeronautics and Space Administration. Lewis Research Center Cleveland, OH United States)
Thomas, Scott R. (National Aeronautics and Space Administration. Lewis Research Center Cleveland, OH United States)
Pack, William D. (National Aeronautics and Space Administration. Lewis Research Center Cleveland, OH United States)
Date Acquired
September 6, 2013
Publication Date
December 1, 1996
Subject Category
Research and Support Facilities (Air)
Report/Patent Number
NAS 1.15:107384
NASA-TM-107384
E-10577
AIAA Paper 97-0565
Meeting Information
Aerospace Sciences Meeting and Exhibit(Reno, NV)
Funding Number(s)
PROJECT: RTOP 505-70-6B
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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