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Numerical optimization of circulation control airfoil at high subsonic speedA numerical procedure for optimizing the design of the circulation control airfoil for use at high subsonic speeds is presented. The procedure consists of an optimization scheme coupled with a viscous potential flow analysis for the blowing jet. The desired airfoil is defined by a combination of three baseline shapes (cambered ellipse and cambered ellipse with drooped and spiraled trailing edges). The coefficients of these shapes are used as design variables in the optimization process. Under the constraints of lift augmentation and lift-to-drag ratios, the airfoil, optimized at free-stream Mach 0.54 and alpha = -2 degrees can be characterized as a cambered ellipse with a drooped trailing edge. Experimental tests support the performance improvement predicted by numerical optimization.
Document ID
19840061411
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Tai, T. C.
(U.S. Navy, David Taylor Naval Ship Research and Development Center Bethesda, MD, United States)
Kidwell, G. H., Jr.
(NASA Ames Research Center Aeronautical Systems Branch, Moffett Field, CA, United States)
Date Acquired
August 12, 2013
Publication Date
August 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 84-2162
Accession Number
84A44198
Distribution Limits
Public
Copyright
Other

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