Subsonic Aeroelastic Analysis of a Thin Flat Plate

Abang Haji Abdul Majid, Dayang Laila (2001) Subsonic Aeroelastic Analysis of a Thin Flat Plate. Masters thesis, Universiti Putra Malaysia.

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Abstract

The interaction between an aircraft structure and the airflow surrounding it has been known to severely affect the stability, performance and manoeuvrability of the aircraft. These interactions form the heart of aero elasticity, a field that comprises all types of aeroelastic phenomena. In this work, a parametric aeroelastic analysis of a thin flat plate clamped at the leading edge and exposed to subsonic airflow was conducted. The aeroelastic effects predicted to occur was flutter, a type of self-excited oscillation. The analysis was simulated using ZAERO, a panel code aeroelastic program, which requires free vibration input, obtained using MSC-NASTRAN, a finite element code. The flutter equation was obtained using Newton's Law of Motion to model the plate while the airflow was modeled using the Small Disturbance Unsteady Aerodynamic Theory. Free vibration results and flutter results obtained were validated against published works found in reference [8, 60 and 61]. The important parameters studied were the aspect ratio and the mass -ratio of the plate. The effect of the number of free vibration modes employed in the analysis was also tested. From the results, it was shown that the flutter velocity decreased as the mass ratio and aspect ratio were increased. The flutter frequency also decreased with higher mass ratio and at large aspect ratio. The use of a higher number of modes in the flutter analysis was found to increase the accuracy of the flutter.

Item Type:Thesis (Masters)
Subject:Aircraft drafting
Subject:Aerolasticity
Chairman Supervisor:Associate Professor ShahNor Basri
Call Number:ITMA 2001 6
Faculty or Institute:Institute of Advanced Technology
ID Code:7978
Deposited By: Nurul Hayatie Hashim
Deposited On:06 Oct 2010 02:06
Last Modified:23 Aug 2011 08:22

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