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Numerical optimization of circulation control airfoilsA numerical procedure for optimizing circulation control airfoils, which consists of the coupling of an optimization scheme with a viscous potential flow analysis for blowing jet, is presented. The desired airfoil is defined by a combination of three baseline shapes (cambered ellipse, and cambered ellipse with drooped and spiralled 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 optimal airfoils are found to lie between those of cambered ellipse and the drooped trailing edge, towards the latter as the angle of attack increases. Results agree qualitatively with available experimental data.
Document ID
19810036136
Document Type
Conference Paper
Authors
Tai, T. C.
(U.S. Naval Material Command, David W. Taylor Naval Ship Research and Development Center Bethesda, Md., United States)
Kidwell, G. H., Jr.
(NASA Ames Research Center Helicopter and Powered Lift System Div., Moffett Field, Calif., United States)
Vanderplaats, G. N.
(U.S. Naval Postgraduate School Monterey, Calif., United States)
Date Acquired
August 11, 2013
Publication Date
January 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 81-0016
Meeting Information
Aerospace Sciences Meeting(St. Louis, MO)
Distribution Limits
Public
Copyright
Other
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