NDLI: The finite element method in low speed aerodynamics

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The finite element method in low speed aerodynamics

Content Provider	NASA Technical Reports Server (NTRS)
Author	Manhardt, P. D. Baker, A. J.
Copyright Year	1975
Description	The finite element procedure is shown to be of significant impact in design of the 'computational wind tunnel' for low speed aerodynamics. The uniformity of the mathematical differential equation description, for viscous and/or inviscid, multi-dimensional subsonic flows about practical aerodynamic system configurations, is utilized to establish the general form of the finite element algorithm. Numerical results for inviscid flow analysis, as well as viscous boundary layer, parabolic, and full Navier Stokes flow descriptions verify the capabilities and overall versatility of the fundamental algorithm for aerodynamics. The proven mathematical basis, coupled with the distinct user-orientation features of the computer program embodiment, indicate near-term evolution of a highly useful analytical design tool to support computational configuration studies in low speed aerodynamics.
File Size	4370733
Page Count	79
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19750018900
Archival Resource Key	ark:/13960/t14n3zh3r
Language	English
Publisher Date	1975-05-01
Access Restriction	Open
Subject Keyword	Aerodynamics Finite Element Method Algorithms Aerodynamic Configurations Wind Tunnels Differential Equations 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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