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Low speed airfoil design and analysisA low speed airfoil design and analysis program was developed which contains several unique features. In the design mode, the velocity distribution is not specified for one but many different angles of attack. Several iteration options are included which allow the trailing edge angle to be specified while other parameters are iterated. For airfoil analysis, a panel method is available which uses third-order panels having parabolic vorticity distributions. The flow condition is satisfied at the end points of the panels. Both sharp and blunt trailing edges can be analyzed. The integral boundary layer method with its laminar separation bubble analog, empirical transition criterion, and precise turbulent boundary layer equations compares very favorably with other methods, both integral and finite difference. Comparisons with experiment for several airfoils over a very wide Reynolds number range are discussed. Applications to high lift airfoil design are also demonstrated.
Document ID
19790011865
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Eppler, R. (Stuttgart Univ. Hampton, VA, United States)
Somers, D. M. (NASA Langley Research Center)
Date Acquired
August 9, 2013
Publication Date
January 1, 1979
Publication Information
Publication: Advanced Technol. Airfoil Res., Vol. 1, Pt. 1
Subject Category
Aerodynamics
Accession Number
79N20036
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19790011859Collected WorksAdvanced Technology Airfoil Research, volume 1, part 1
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