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Experimental Analysis of a Rocket Based Combined Cycle (RBCC) Engine in a Direct-Connect Test FacilityThe object of this study is to investigate the operation of a RBCC at ramjet and scramjet flight conditions using a direct-connect test facility. The apparatus being tested is a single strut-rocket within a dual-mode ram/scramjet combustor. The gaseous hydrogen/oxygen, linear strut-rocket was supplied by Aerojet Propulsion Company. The hardware is being tested in the Direct Connect Supersonic Combustion Test Facility at NASA Langley Research Center. The test facilities hydrogen/oxygen vitiated heater is capable of flight total enthalpies to Mach 8. A Mach 2.5 facility nozzle mates the heater to the combustor duct. The rocket ejector will ordinarily operate in a fuel-rich mode. Additional fuel injection is provided by a pair of parallel injectors located at the base of the strut body. Instrumentation on the test apparatus includes a unique, direct thrust measurement system. Performance predictions for the anticipated test conditions have been made using a one-dimensional, thermodynamic analysis code. Results from the code show the dependence of overall thrust and specific impulse on rocket chamber pressure, rocket fuel equivalence ratio, and overall fuel equivalence ratio. Once the experimental test series begins, the inferred combustion efficiency as a function of axial location and the thermal choke region (where applicable) can also be determined using this code. Upon completion of the experimental test series, measurements will be used to calculate thrust, specific impulse, etc. Measured and calculated values will be compared to those found analytically. If appropriate, the code will be tailored to better predict hardware operation. Conclusions will be drawn as to the fuel-rich rocket's overall effect on ramjet and scramjet performance. Also, comparisons will be made between the integrated thrust calculated from the static pressure taps located along the duct and the thrust measured by the direct thrust measurement system.
Document ID
19990064401
Acquisition Source
Marshall Space Flight Center
Document Type
Conference Paper
Authors
K. Nelson
(University of Alabama in Huntsville Huntsville, Alabama, United States)
Clark W. Hawk
(University of Alabama in Huntsville Huntsville, Alabama, United States)
Date Acquired
August 18, 2013
Publication Date
October 27, 1997
Subject Category
Aircraft Propulsion And Power
Meeting Information
Meeting: 34th JANNAF Airbreathing Propulsion Subcommittee Meeting
Location: West Palm Beach, FL
Country: US
Start Date: October 27, 1997
End Date: October 31, 1997
Sponsors: United States Department of the Army, United States Department of the Air Force, United States Department of the Navy, National Aeronautics and Space Administration
Distribution Limits
Public
Copyright
Content with NO Permission

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