Fast Viscous Correction Method for Unsteady Transonic Flow About Airfoils

Author

S. C. Lee, Missouri University of Science and TechnologyFollow

Abstract

This study modified the inviscid, small-disturbance, unsteady, transonic code, LTRAN2, to consider the viscous effect. The boundary condition of the vertical surface velocity needs to include an additional term which is derived from the effective displacement thickness of the boundary layer. The effective thickness consists of a viscous wedge to simulate the suddenly thickened boundary layer behind a shock and a displacement thickness obtained from a conventional integral boundary-layer method. Unsteady aerodynamic performances were calculated for several airfoils. Comparisons were made with experimental data of two supercritical airfoils. The viscous solutions gave better agreement with experimental data with practically no increase in computational time.

Recommended Citation

S. C. Lee, "Fast Viscous Correction Method for Unsteady Transonic Flow About Airfoils," AIAA Journal, American Institute of Aeronautics and Astronautics (AIAA), Jan 1984.

The definitive version is available at https://doi.org/10.2514/3.48508

Department(s)

Mechanical and Aerospace Engineering

International Standard Serial Number (ISSN)

0001-1452

Document Type

Article - Journal

Document Version

Citation

File Type

text

Language(s)

English

Rights

© 1984 American Institute of Aeronautics and Astronautics (AIAA), All rights reserved.

Publication Date

01 Jan 1984