NDLI: Three dimensional steady and unsteady asymmetric flow past wings of arbitrary planforms

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Three dimensional steady and unsteady asymmetric flow past wings of arbitrary planforms

Content Provider	NASA Technical Reports Server (NTRS)
Author	Atta, E. H. Nayfeh, A. H. Kandil, O. A.
Copyright Year	1977
Description	The nonlinear discrete vortex method was extended to treat the problem of asymmetric flows past a wing with leading-edge separation, including steady and unsteady flows. The problem was formulated in terms of a body-fixed frame of reference, and the nonlinear discrete vortex method was modified accordingly. Only examples of flows past delta wings are presented. Comparison of these results with experimental results for a delta wing undergoing a steady rolling motion at zero angle of attack demonstrates the superiority of the present method in obtaining highly accurate loads. Numerical results for yawed wings at large angles of attack are also presented. In all cases, total load coefficients, pressure distributions and shapes of the free-vortex sheets are shown.
File Size	1092473
Page Count	34
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19770026158
Archival Resource Key	ark:/13960/t94796305
Language	English
Publisher Date	1977-09-01
Access Restriction	Open
Subject Keyword	Aerodynamics Vortex Sheets Numerical Analysis Asymmetry Three Dimensional Flow Delta Wings Steady Flow Pressure Distribution Unsteady Flow Flow Geometry Leading Edges Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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