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Effect of Flow Misalignment and Multi-Hole Interaction on Boundary-Layer Bleed Hole Flow Coefficient BehaviorThe effect of flow misalignment on the flow coefficient behavior of a 20 deg. boundary-layer bleed hole and the effect of the interaction between two 90 deg. bleed holes separated by two hole diameters on flow coefficient behavior has been studied experimentally. Both tests were run at freestream Mach numbers of 0.61, 1.62 and 2.49. The flow misalignment study was conducted over a range of 0 to 30 deg. The results show that neither flow misalignment nor hole interaction has much effect on the flow coefficient for the subsonic case. For the supersonic cases, flow misalignment causes significant degradation in the performance of the slant hole. For the supersonic normal hole interaction cases, depending on the hole orientation, either an increase or decrease in overall flow coefficient was observed. The largest change in flow coefficient, 6% increase at near choke conditions, occurred when the holes were oriented in line with the flow direction.
Document ID
19970025061
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Davis, David O. (NASA Lewis Research Center Cleveland, OH United States)
Grimes, Marcus (Military Academy West Point, NY United States)
Schoenenberger, Mark (Case Western Reserve Univ. Cleveland, OH United States)
Date Acquired
September 6, 2013
Publication Date
June 1, 1997
Subject Category
Aircraft Propulsion And Power
Report/Patent Number
E-10768
NAS 1.15:107480
NASA-TM-107480
Meeting Information
Meeting: Mechanical Engineeringm Congress and Exhibit
Location: Atlanta, GA
Country: United States
Start Date: November 17, 1996
End Date: November 22, 1996
Sponsors: American Society of Mechanical Engineers
Accession Number
97N24713
Funding Number(s)
PROJECT: RTOP 523-36-13
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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