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Parametric Data from a Wind Tunnel Test on a Rocket-Based Combined-Cycle Engine InletA 40-percent scale model of the inlet to a rocket-based combined-cycle (RBCC) engine was tested in the NASA Glenn Research Center 1- by 1-Foot Supersonic Wind Tunnel (SWT). The full-scale RBCC engine is scheduled for test in the Hypersonic Tunnel Facility (HTF) at NASA Glenn's Plum Brook Station at Mach 5 and 6. This engine will incorporate the configuration of this inlet model which achieved the best performance during the present experiment. The inlet test was conducted at Mach numbers of 4.0, 5.0, 5.5, and 6.0. The fixed-geometry inlet consists of an 8 deg.. forebody compression plate, boundary layer diverter, and two compressive struts located within 2 parallel sidewalls. These struts extend through the inlet, dividing the flowpath into three channels. Test parameters investigated included strut geometry, boundary layer ingestion, and Reynolds number (Re). Inlet axial pressure distributions and cross-sectional Pitot-pressure surveys at the base of the struts were measured at varying back-pressures. Inlet performance and starting data are presented. The inlet chosen for the RBCC engine self-started at all Mach numbers from 4 to 6. Pitot-pressure contours showed large flow nonuniformity on the body-side of the inlet. The inlet provided adequate pressure recovery and flow quality for the RBCC cycle even with the flow separation.
Document ID
20020006304
Acquisition Source
Glenn Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Fernandez, Rene (NASA Glenn Research Center Cleveland, OH United States)
Trefny, Charles J. (NASA Glenn Research Center Cleveland, OH United States)
Thomas, Scott R. (NASA Glenn Research Center Cleveland, OH United States)
Bulman, Mel J. (Aerojet-General Corp. Sacramento, CA United States)
Date Acquired
September 7, 2013
Publication Date
November 1, 2001
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
E-10144
NASA/TM-2001-107181
NAS 1.15:107181
Meeting Information
Meeting: 1995 Airbreathing Propulsion Subcommittee Meeting
Location: Tampa, FL
Country: United States
Start Date: December 5, 1995
End Date: December 9, 1995
Sponsors: NASA Headquarters, Department of the Navy, Department of the Air Force, Department of the Army
Funding Number(s)
PROJECT: RTOP 708-48-13
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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