Airfoil Geometry and Flow Compressibility Effects on Wing and Blade Flutter
Loading...
Authors
Jones, K.D.
Platzer, M.F.
Subjects
Advisors
Date of Issue
1998
Date
1998
Publisher
Language
Abstract
An unsteady, two-dimensional, incompressible potential-flow solver and an unsteady, two-dimensional, compressible Euler/Navier-Stokes flow solver are coupled with a two-degree-of-freedom structural model for the time-domain computation of aeroelastic response. Comparisons are made between results from the two flow solvers and with flutter boundary predictions of linear theory. Presented results demonstrate similar destabilizing effects for both increasing airfoil thickness and increasing Mach number. More importantly, it is shown that linear theory yields un-conservative flutter-velocity predictions. While linear theory predicts that single-degree-of-freedom (pitching) flutter cannot occur except with an unrealistically high sectional moment of inertia, it is shown here that thicker airfoils in compressible flows may easily achieve single-degree-of-freedom flutter under realistic conditions.
Type
Conference Paper
Description
AIAA Paper No. 98-0517, 36th AIAA Aerospace Sciences Meeting, Reno, Nevada, Jan. 1998.
Series/Report No
Department
Department of Mechanical and Aerospace Engineering
Organization
Identifiers
NPS Report Number
Sponsors
Funder
Format
Citation
Jones, K.D. and Platzer, M.F., "Airfoil Geometry and Flow Compressibility Effects on Wing and Blade Flutter," AIAA Paper No. 98-0517, 36th AIAA Aerospace Sciences Meeting, Reno, Nevada, Jan. 1998.
Distribution Statement
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.