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Aircraft flutter suppression using plasma

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  • Full or part time
    Dr W Wang
  • Application Deadline
    Applications accepted all year round
  • Self-Funded PhD Students Only
    Self-Funded PhD Students Only

About This PhD Project

Project Description

Aircrafts can be lighter when composites are using. The structure would become more ‘flexible’, particularly for the wings. To prevent catastrophic structural failure from resonance coupled with aerodynamic loads, prevention and suppression of flutter are critical to design and operate air vehicles. In this project, we are proposing a novel approach to control the boundary layer of air flow so that flutter of a wing may be suppressed.

Project Aims and Objectives

Design against flutter is crucial for flexible structures when coupling with aerodynamics. Some common approaches to reduce flutter are via active structure control. For example, one can actively control a flap along the tailing edge of a wing to alter the airflow, and then the aerodynamics force changes, so that the flutter may be reduced. The active control of this approach can be complicated because both the structure and the airflow are changing. We are proposing a new approach in this project. We are not going to actively control the structure but we can change the airflow by using plasma. If you are interested in the area, please contact us for further details

Entry Requirements

First degree (2:1 or above) in Mechanical Engineering or in Applied Mathematics
Good understanding of structural and fluid Mechanics

Informal enquiries can be made to
Tel: +44 161 247 1533 email [Email Address Removed]

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