Date of Award

Summer 1991

Document Type

Thesis

Degree Name

Master of Science (MS)

Department

Mechanical & Aerospace Engineering

Program/Concentration

Mechanical Engineering

Committee Director

Chuh Mei

Committee Member

M-Nabil Hamouda

Committee Member

Gene Hou

Call Number for Print

Special Collections; LD4331.E56S61

Abstract

A wind tunnel model based on a trail rotor vehicle concept was tested for wing flutter in the subsonic flow regime. The wind tunnel model was flutter tested in the forward flight mode only. From this test it was determined that this conceptual vehicle may be susceptible to wing flutter. However, the flutter encountered was not catastrophic but was of the limited amplitude type. The trailing rotor blades were found to have a positive aerodynamic damping effect on flutter. The flutter mechanism for each flutter point was due to a coupling of the first wing bending and first wing torsion vibration modes. A current flutter analysis method was used to make predictions of the flutter boundary. This method was found to be adequate for making flutter predictions for this type of vehicle. Good correlation between the analysis and the experimental data was shown.

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In Copyright. URI: http://rightsstatements.org/vocab/InC/1.0/ This Item is protected by copyright and/or related rights. You are free to use this Item in any way that is permitted by the copyright and related rights legislation that applies to your use. For other uses you need to obtain permission from the rights-holder(s).

DOI

10.25777/zj0a-bs22

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