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Calculated Low-Speed Steady and Time-Dependent Aerodynamic Derivatives for Some Airfoils Using a Discrete Vortex MethodThis paper contains a collection of some results of four individual studies presenting calculated numerical values for airfoil aerodynamic stability derivatives in unseparated inviscid incompressible flow due separately to angle-of-attack, pitch rate, flap deflection, and airfoil camber using a discrete vortex method. Both steady conditions and oscillatory motion were considered. Variables include the number of vortices representing the airfoil, the pitch axis / moment center chordwise location, flap chord to airfoil chord ratio, and circular or parabolic arc camber. Comparisons with some experimental and other theoretical information are included. The calculated aerodynamic numerical results obtained using a limited number of vortices provided in each study compared favorably with thin airfoil theory predictions. Of particular interest are those aerodynamic results calculated herein (such as induced drag) that are not readily available elsewhere.
Document ID
20160001631
Acquisition Source
Langley Research Center
Document Type
Technical Memorandum (TM)
Authors
Riley, Donald R.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
February 5, 2016
Publication Date
December 1, 2015
Subject Category
Fluid Mechanics And Thermodynamics
Report/Patent Number
L-20616
NF1676L-22665
NASA/TM-2015-218998
Funding Number(s)
WBS: WBS 432938.11.01.07.43.40.17
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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