A Computational Method for Wings of Arbitrary Planform.
Abstract
The computational method developed in this thesis permits the calculation of the aerodynamic performance of a wing of arbitrary planform. Both basic and additional lift are analyzed. This treaties 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 used to determine these discrete values. Control point indeterminacies are evaluated analytically. Matrix inversion is required for solution by the method presented. 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. Keywords include: Wing aerodynamics; and Lifting surface;
Document Details
- Document Type
- Technical Report
- Publication Date
- Dec 01, 1984
- Accession Number
- ADA153788
Entities
People
- C. S. Jones
Organizations
- Naval Postgraduate School