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A vortex-filament and core model for wings with edge vortex separationA method for predicting aerodynamic characteristics of slender wings with edge vortex separation was developed. Semiempirical but simple methods were used to determine the initial positions of the free sheet and vortex core. Comparison with available data indicates that: the present method is generally accurate in predicting the lift and induced drag coefficients but the predicted pitching moment is too positive; the spanwise lifting pressure distributions estimated by the one vortex core solution of the present method are significantly better than the results of Mehrotra's method relative to the pressure peak values for the flat delta; the two vortex core system applied to the double delta and strake wing produce overall aerodynamic characteristics which have good agreement with data except for the pitching moment; and the computer time for the present method is about two thirds of that of Mehrotra's method.
Document ID
19820004166
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Pao, J. L. (Kansas Univ. Center for Research, Inc. Lawrence, KS, United States)
Lan, C. E. (Kansas Univ. Center for Research, Inc. Lawrence, KS, United States)
Date Acquired
September 4, 2013
Publication Date
November 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-164980
CRINC-FRL-424-1
Accession Number
82N12039
Funding Number(s)
CONTRACT_GRANT: NCC1-18
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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