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Improving CAP-TSD steady pressure solutions through airfoil slope modificationA modification of airfoil section geometry is examined for improvement of the leading edge pressures predicted by the Computational Aeroelasticity Program - Transonic Small Disturbance (CAP-TSD). Results are compared with Eppler solutions to assess improvement. Preliminary results indicate that a fading function modification of section slopes is capable of significant improvements in the pressures near the leading edge computed by CAP-TSD. Application of this modification to airfoil geometry before use in CAP-TSD is shown to reduce the nonphysical pressure peak predicted by the transonic small disturbance solver. A second advantage of the slope modification is the substantial reduction in sensitivity of CAP-TSD steady pressure solutions to the computational mesh.
Document ID
19960049881
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Mitterer, Kent F. (Pennsylvania State Univ. State College, PA United States)
Maughmer, Mark D. (Pennsylvania State Univ. State College, PA United States)
Silva, Walter A. (NASA Langley Research Center Hampton,VA United States)
Batina, John T. (NASA Langley Research Center Hampton,VA United States)
Date Acquired
September 6, 2013
Publication Date
August 1, 1996
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:110214
NASA-TM-110214
Accession Number
96N34082
Funding Number(s)
PROJECT: RTOP 505-63-50-13
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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