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Experimental Investigation of the Application of Microramp Flow Control to an Oblique Shock InteractionThe effectiveness of microramp flow control devices in controlling an oblique shock interaction was tested in the 15- by 15-Centimeter Supersonic Wind Tunnel at NASA Glenn Research Center. Fifteen microramp geometries were tested varying the height, chord length, and spacing between ramps. Measurements of the boundary layer properties downstream of the shock reflection were analyzed using design of experiments methods. Results from main effects, D-optimal, full factorial, and central composite designs were compared. The designs provided consistent results for a single variable optimization.
Document ID
20090042751
Document Type
Technical Memorandum (TM)
Authors
Hirt, Stefanie M.
(NASA Glenn Research Center Cleveland, OH, United States)
Anderson, Bernhard H.
(NASA Glenn Research Center Cleveland, OH, United States)
Date Acquired
August 24, 2013
Publication Date
November 1, 2009
Subject Category
Aerodynamics
Report/Patent Number
E-16942
AIAA Paper 2009-919
NASA/TM-2009-215630
Meeting Information
47th Aerospace Sciences Meeting(Orlando, FL)
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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