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Comparison of the full potential and Euler formulations for computing transonic airfoil flowsA quantitative comparison between the Euler and full potential formulations with respect to speed and accuracy is presented. The robustness of the codes used is tested by a number of transonic airfoil cases. The computed results are from four transonic airfoil computer codes. The full potential codes use fully implicit iteration algorithms. The first Euler code uses a fully implicit ADI iteration scheme. The second Euler code uses an explicit Runge Kutta time stepping algorithm which is enhanced by a multigrid convergence acceleration scheme. Quantitative comparisons are made using various plots of lift coefficient versus the average mesh spacing along the airfoil. Besides yielding an asymptotic limit to the lift coefficient, these results also demonstrate the truncation error behavior of the various codes. Quantitative conclusions regarding the full potential and Euler formulations with respect to accuracy, speed, and robustness can be presented.
Document ID
19840023024
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Flores, J. (NASA Ames Research Center Moffett Field, CA, United States)
Barton, J. (NASA Ames Research Center Moffett Field, CA, United States)
Holst, T. L. (NASA Ames Research Center Moffett Field, CA, United States)
Pulliam, T. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
September 4, 2013
Publication Date
June 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:85983
A-9816
NASA-TM-85983
Accession Number
84N31094
Funding Number(s)
PROJECT: RTOP 505-31-01-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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