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A direct and inverse boundary layer method for subsonic flow over delta wingsA new inverse boundary layer method is developed and applied to incompressible flows with laminar separation and reattachment. Test cases for two dimensional flows are computed and the results are compared with those of other inverse methods. One advantage of the present method is that the calculation of the inviscid velocities may be determined at each marching step without having to iterate. The inverse method was incorporated with the direct method to calculate the incompressible, conical flow over a slender delta wing at incidence. The location of the secondary separation line on the leeward surface of the wing is determined and compared with experiment for a unit aspect ratio wing at 20.5 deg incidence. The viscous flow in the separated region was calculated using prescribed skin friction coefficients.
Document ID
19860017723
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Woodson, S. H. (North Carolina State Univ. Raleigh, NC, United States)
Dejarnette, F. R. (North Carolina State Univ. Raleigh, NC, United States)
Date Acquired
August 12, 2013
Publication Date
July 1, 1986
Publication Information
Publication: NASA. Langley Research Center Vortex Flow Aerodynamics, Vol. 1
Subject Category
Aerodynamics
Accession Number
86N27195
Funding Number(s)
CONTRACT_GRANT: NCC1-22
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19860017718Collected WorksVortex Flow Aerodynamics, volume 1
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