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Effect of airfoil (trailing-edge) thickness on the numerical solution of panel methods based on the Dirichlet boundary conditionThe practical limit of airfoil thickness ratio for which acceptable engineering results are obtainable with the Dirichlet boundary-condition-based numerical methods is investigated. This is done by studying the effect of thickness on the calculated pressure distribution near the trailing edge and by comparing the aerodynamic coefficients with available exact solutions. The first objective of this study, owing to the wide use of such computational methods, is to demonstrate the numerical symptoms that occur when the body or wing thickness approaches zero and to increase the awareness of potential users of these methods. Additionally, an effort is made to obtain the practical limits of the trailing-edge thickness where such problems will appear in the flow solution, and to propose some possible cures for very thin airfoils or those with cusped trailing edges.
Document ID
19920045417
Acquisition Source
Legacy CDMS
Document Type
Reprint (Version printed in journal)
Authors
Yon, Steven
(NASA Ames Research Center Moffett Field, CA, United States)
Katz, Joseph
(NASA Ames Research Center Moffett Field, CA, United States)
Plotkin, Allen
(San Diego State University CA, United States)
Date Acquired
August 15, 2013
Publication Date
March 1, 1992
Publication Information
Publication: AIAA Journal
Volume: 30
ISSN: 0001-1452
Subject Category
Aerodynamics
Accession Number
92A28041
Funding Number(s)
CONTRACT_GRANT: NCC2-596
Distribution Limits
Public
Copyright
Other

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