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Research on Supersonic Inlet BleedPhase I data results of the Fundamental Inlet Bleed Experiments project at NASA Glenn Research Center (GRC) are presented which include flow coefficient results for two single-hole boundary-layer bleed configurations. The bleed configurations tested are round holes at inclination angles of 90deg and 20deg both having length-to-diameter ratios of 2.0. Results were obtained at freestream Mach numbers of 1.33, 1.62, 1.98, 2.46, and 2.92 and unit Reynolds numbers of 0.984, 1.89, and 2.46 10(exp 7)/m. Approach boundary-layer data are presented for each flow condition and the flow coefficient results are compared to existing multi-hole data obtained under similar conditions. For the 90deg hole, the single and multi-hole distributions agree fairly well with the exception that under supercritical operation, the multi-hole data chokes at higher flow coefficient levels. This behavior is also observed for the 20deg hole but to a lesser extent. The 20deg hole also shows a markedly different characteristic at subcritical operation. Also presented are preliminary results of a Computational Fluid Dynamics (CFD) analysis of both configurations at the Mach 1.33 and a unit Reynolds number of 2.46 10(exp 7)/m. Comparison of the results shows the agreement to be very good.
Document ID
20120013594
Document Type
Technical Memorandum (TM)
Authors
Davis, David O.
(NASA Glenn Research Center Cleveland, OH, United States)
Vyas, Manan A.
(NASA Glenn Research Center Cleveland, OH, United States)
Slater, John W.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 26, 2013
Publication Date
August 1, 2012
Subject Category
Aerodynamics
Report/Patent Number
NASA/TM-2012-217620
AIAA Paper 2012-0272
E-18208
Meeting Information
50th Aerospace Sciences Meeting(Nashville, TN)
Funding Number(s)
WBS: WBS 984754.02.07.03.13.02
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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