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Tangential blowing for control of strong normal shock - Boundary layer interactions on inlet rampsThe use of tangential blowing from a row of holes in an aft facing step is found to provide good control of the ramp boundary layer, normal shock interaction on a fixed geometry inlet over a wide range of inlet mass flow ratios. Ramp Mach numbers of 1.36 and 1.96 are investigated. The blowing geometry is found to have a significant effect on system performance at the highest Mach number. The use of high-temperature air in the blowing system, however, has only a slight effect on performance. The required blowing rates are significantly high for the most severe test conditions. In addition, the required blowing coefficient is found to be proportional to the normal shock pressure rise.
Document ID
19820054149
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Schwendemann, M. F.
(Northrop Corp. Hawthorne, CA, United States)
Sanders, B. W.
(NASA Lewis Research Center Cleveland, OH, United States)
Date Acquired
August 10, 2013
Publication Date
June 1, 1982
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 82-1082
Meeting Information
Meeting: Joint Propulsion Conference
Location: Cleveland, OH
Start Date: June 21, 1982
End Date: June 23, 1982
Sponsors: AIAA, SAE, and ASME
Accession Number
82A37684
Funding Number(s)
CONTRACT_GRANT: NAS2-9281
Distribution Limits
Public
Copyright
Other

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