NASA Logo

NTRS - NASA Technical Reports Server

Back to Results
VORCAM: A computer program for calculating vortex lift effect of cambered wings by the suction analogyA user's guide to an improved version of Woodward's chord plane aerodynamic panel computer code is presumed. The guide can be applied to cambered wings exhibiting edge separated flow, including those with leading edge vortex flow at subsonic and supersonic speeds. New orientations for the rotated suction force are employed based on the momentum principal. The supersonic suction analogy method is improved by using an effective angle of attack defined through a semiempirical method.
Document ID
19840025316
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Lan, C. E. (Kansas Univ. Center for Research, Inc. Lawrence, KS, United States)
Chang, J. F. (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
CRINC-FRL-426-2
NAS 1.26:165800
NASA-CR-165800
Report Number: CRINC-FRL-426-2
Report Number: NAS 1.26:165800
Report Number: NASA-CR-165800
Accession Number
84N33387
Funding Number(s)
PROJECT: RTOP 505-31-43
CONTRACT_GRANT: NSG-1629
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

Related Records

There are no records associated with this record.
No Preview Available