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A comparison of computer-generated lift and drag polars for a Wortmann airfoil to flight and wind tunnel resultsComputations of drag polars for a low-speed Wortmann sailplane airfoil are compared to both wind tunnel and flight results. Excellent correlation is shown to exist between computations and flight results except when separated flow regimes were encountered. Wind tunnel transition locations are shown to agree with computed predictions. Smoothness of the input coordinates to the PROFILE airfoil analysis computer program was found to be essential to obtain accurate comparisons of drag polars or transition location to either the flight or wind tunnel results.
Document ID
19860019447
Acquisition Source
Legacy CDMS
Document Type
Contractor Report (CR)
Authors
Bowers, A. H. (California Polytechnic State Univ. San Luis Obispo, CA, United States)
Sandlin, D. R. (California Polytechnic State Univ. San Luis Obispo, CA, United States)
Date Acquired
September 5, 2013
Publication Date
June 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:176963
NASA-CR-176963
Accession Number
86N28919
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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