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Hyper-X Mach 10 Engine Flowpath Development: Fifth Entry Test Conditions and MethodologyA series of Hyper-X Mach 10 flowpath ground tests are underway to obtain engine performance and operation data and to confirm and refine the flowpath design methods. The model used is a full-scale height, partial-width replica of the Hyper-X Research Vehicle propulsive flowpath with truncated forebody and aftbody. This is the fifth test entry for this model in the NASA-HYPULSE facility at GASL. For this entry the facility nozzle and model forebody were modified to better simulate the engine inflow conditions at the target flight conditions. The forebody was modified to be a wide flat plate with no flow fences, the facility nozzle Mach number was increased, and the model was positioned to be tested in a semi-direct-connect arrangement. This paper presents a review of the test conditions, model calibrations, and a description of steady flow confirmation. The test series included runs using hydrogen fuel, and a silane-in-hydrogen fuel mixture. Other test parameters included the model mounting angle (relative to the tunnel flow), and the test gas oxygen fraction to account for the presence of [NO] in the test gas at the M10 conditions.
Document ID
20010058924
Acquisition Source
Langley Research Center
Document Type
Preprint (Draft being sent to journal)
Authors
Bakos, R. J. (General Applied Science Labs., Inc. Ronkonkoma, NY United States)
Tsai, C.-Y. (General Applied Science Labs., Inc. Ronkonkoma, NY United States)
Rogers, R. C. (NASA Langley Research Center Hampton, VA United States)
Shih, A. T. (NASA Langley Research Center Hampton, VA United States)
Date Acquired
September 7, 2013
Publication Date
January 1, 2001
Subject Category
Aircraft Design, Testing And Performance
Report/Patent Number
AIAA Paper 2001-1814
Meeting Information
Meeting: 10th AIAA/NAL-NASDA-ISAS International Space Planes and Hypersonic Systems and Technologies Conference Committee
Location: Kyoto
Country: Japan
Start Date: April 24, 2001
End Date: April 27, 2001
Sponsors: Tokyo Univ., National Space Development Agency, American Inst. of Aeronautics and Astronautics, National Aeronautical Lab.
Distribution Limits
Public
Copyright
Public Use Permitted.

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