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Calculating the Vortex Lift Effect of Cambered WingsComputer program VORCAM calculates vortex-lift effect of cambered wings by suction analogy. Based on improved version of Woodward's chord plane aerodynamic panel method for subsonic and superrsonic flow. Developed specifically for cambered wings exhibitig edge-separated vortex flow, including those with leading-edge vortex flaps. Program written in FORTRAN IV.
Document ID
19830000082
Acquisition Source
Legacy CDMS
Document Type
Other - NASA Tech Brief
Authors
Lan, C. E. (University of Kansas Center for Research, Inc.)
Chang, J. F. (University of Kansas Center for Research, Inc.)
Date Acquired
August 11, 2013
Publication Date
August 1, 1983
Publication Information
Publication: NASA Tech Briefs
Volume: 7
Issue: 3
ISSN: 0145-319X
Subject Category
Mechanics
Report/Patent Number
LAR-12985
Report Number: LAR-12985
ISSN: 0145-319X
Accession Number
83B10082
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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