A computational method for wings of arbitrary planform
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Authors
Jones, Christopher Stephen
Subjects
Lifting surface
Wing aerodynamics
Wing aerodynamics
Advisors
Gawain, T.H.
Date of Issue
1984-12
Date
December 1984
Publisher
Language
en_US
Abstract
The computational method developed in this thesis permits the calculation of the aerodynamic performance of a wing of arbitrary platform. Both basic and additional lift are analyzed. This treatise is restricted to thin wings
in steady, inviscid, incompressible flow. The method uses a grid system of control points over the wing semi-span. The circulation over the wing is considered variable with discrete values at the specified grid points. Finite difference equations are utilized to determine these discrete values. Control point indeterminacies are evaluated analytically. Matrix inversion is required for solution by the method presented. Details of the matrix technique are developed in Ref. 4. A brief summary of the principal computational relations is included. No numerical results are yet available but are expected during the next phase of this research.
Type
Thesis
Description
Series/Report No
Department
Aeronautics
Organization
Naval Postgraduate School (U.S.)
Identifiers
NPS Report Number
Sponsors
Funder
Format
Citation
Distribution Statement
Approved for public release; distribution is unlimited.
Rights
This publication is a work of the U.S. Government as defined in Title 17, United States Code, Section 101. Copyright protection is not available for this work in the United States.