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Drag calculations of wings using Euler methodsSeveral techniques for the calculation of drag using Euler-equation formulations are discussed and compared. Surface-pressure integration (a nearfield technique) as well as two different farfield calculation techniques are described and applied to three-dimensional flow-field solutions for an aspect-ratio-7 wing with attached flow. The present calculations are limited to steady, low-Mach-number flows around three-dimensional configurations in the absence of active systems such as surface blowing/suction and propulsion. Although the main focus of the paper is the calculation of aerodynamic drag, the calculation of aerodynamic lift is also briefly discussed. Three Euler methods are used to obtain the flowfield solutions. The farfield technique based on the evaluation of a wake-integral appears to provide the most consistent and accurate drag predictions.
Document ID
19910034617
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Van Dam, C. P.
(California, University Davis, United States)
Chang, I. C.
(NASA Ames Research Center Moffett Field, CA, United States)
Vijgen, P. M. H. W.
(High Technology Corp. Hampton, VA, United States)
Nikfetrat, Koorosh
(California Univ. Davis, CA, United States)
Date Acquired
August 15, 2013
Publication Date
January 1, 1991
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 91-0338
Accession Number
91A19240
Funding Number(s)
CONTRACT_GRANT: NAS1-18240
CONTRACT_GRANT: NCA2-387
Distribution Limits
Public
Copyright
Other

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