Effect Of Thickness On The Unsteady Aerodynamics Of Closely Coupled Oscillating Airfoils

Abstract

A vortex panel method is presented for the solution of incompressible unsteady aerodynamic problems for airfoils with finite thickness. The accuracy and robustness of the method is demonstrated through comparisons with the existing numerical data and independent test cases. Also, through numerous examples, the flexibility of this method in handling different types of trailing-edge shapes and multiple interfering geometries is shown. Furthermore, the method is used to analyze the effects of airfoil thickness on aerodynamic coefficients of multielement or multiple airfoils. It is shown that, although the influence of thickness is negligible for single element airfoils, it can be profound for closely coupled airfoils and slotted flaps. © 1988 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

Department(s)

Mechanical and Aerospace Engineering

International Standard Serial Number (ISSN)

0021-8669

Document Type

Article - Journal

Document Version

Citation

File Type

text

Language(s)

English

Rights

© 2023 American Institute of Aeronautics and Astronautics, All rights reserved.

Publication Date

01 Jan 1991

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