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Leading-edge slat optimization for maximum airfoil liftA numerical procedure for determining the position (horizontal location, vertical location, and deflection) of a leading edge slat that maximizes the lift of multielement airfoils is presented. The structure of the flow field is calculated by iteratively coupling potential flow and boundary layer analysis. This aerodynamic calculation is combined with a constrained function minimization analysis to determine the position of a leading edge slat so that the suction peak on the nose of the main airfoil is minized. The slat position is constrained by the numerical procedure to ensure an attached boundary layer on the upper surface of the slat and to ensure negligible interaction between the slat wake and the boundary layer on the upper surface of the main airfoil. The highest angle attack at which this optimized slat position can maintain attached flow on the main airfoil defines the optimum slat position for maximum lift. The design method is demonstrated for an airfoil equipped with a leading-edge slat and a trailing edge, single-slotted flap. The theoretical results are compared with experimental data, obtained in the Ames 40 by 80 Foot Wind Tunnel, to verify experimentally the predicted slat position for maximum lift. The experimentally optimized slat position is in good agreement with the theoretical prediction, indicating that the theoretical procedure is a feasible design method.
Document ID
19790018929
Document Type
Technical Memorandum (TM)
Authors
Olson, L. E.
(NASA Ames Research Center Moffett Field, CA, United States)
Mcgowan, P. R.
(Computer Sci. Corp. Mountain View, Calif., United States)
Guest, C. J.
(Computer Sci. Corp. Mountain View, Calif., United States)
Date Acquired
September 3, 2013
Publication Date
July 1, 1979
Subject Category
Aerodynamics
Report/Patent Number
A-7753
NASA-TM-78566
Funding Number(s)
PROJECT: RTOP 505-06-31
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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