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A generalized vortex lattice method for subsonic and supersonic flow applicationsIf the discrete vortex lattice is considered as an approximation to the surface-distributed vorticity, then the concept of the generalized principal part of an integral yields a residual term to the vorticity-induced velocity field. The proper incorporation of this term to the velocity field generated by the discrete vortex lines renders the present vortex lattice method valid for supersonic flow. Special techniques for simulating nonzero thickness lifting surfaces and fusiform bodies with vortex lattice elements are included. Thickness effects of wing-like components are simulated by a double (biplanar) vortex lattice layer, and fusiform bodies are represented by a vortex grid arranged on a series of concentrical cylindrical surfaces. The analysis of sideslip effects by the subject method is described. Numerical considerations peculiar to the application of these techniques are also discussed. The method has been implemented in a digital computer code. A users manual is included along with a complete FORTRAN compilation, an executed case, and conversion programs for transforming input for the NASA wave drag program.
Document ID
19780008059
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Miranda, L. R. (Lockheed-California Co. Burbank, CA, United States)
Elliot, R. D. (Lockheed-California Co. Burbank, CA, United States)
Baker, W. M. (Lockheed-California Co. Burbank, CA, United States)
Date Acquired
September 3, 2013
Publication Date
December 1, 1977
Subject Category
Aerodynamics
Report/Patent Number
NASA-CR-2865
LR-28112
Accession Number
78N16002
Funding Number(s)
CONTRACT_GRANT: NAS1-12972
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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