Simulations aéroélastiques d’ailes oscillantes multi-segments par méthode vortex

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Authors
  1. Morisette, J-F.
Corporate Authors
Defence R&D Canada - Valcartier, Valcartier QUE (CAN);Laval Univ, Quebec QUE (CAN) Departement de Genie Mecanique
Abstract
The research presented in this master thesis is aimed to study chordwise flexibility effect on flapping-wings aerodynamics in low Reynolds number propulsion regime for nano-air vehicle applications. To do so, an appropriate aeroelastic modelling tool had to be implemented. The main idea of this project is to consider a discrete flexibility using an articulated wing composed of rigid segments linked together by elastic torsional joints. This approach means solving rigid body dynamics coupled with an incompressible flow. The lagrangian vortex particles method is used to solve the flow around multiple arbitrarily moving rigid bodies. The fluid-structure coupling implemented allows to take into account N rigid segments which dynamics is governed by an imposed motion on one of them, by instantaneous aerodynamic forces generated by the flow and by elastic forces in the hinges. Adding an extra subiteration loop to the vortex method was necessary to ensure a “strong” coupling fluid-structure interaction (FSI). The development of such a tool was used to study the impact of various discrete flexibility parameters in flapping-wing propulsion at low Reynolds number. We see that it is possible to improve oscillating wing performances in propulsion (in thrust or in efficiency) by modifying location or stiffness of the elastic hinges as well as solid to fluid density ratio of the rigid bodies. This work opens the way toward optimization of chordwise flexibility distribution for aerodyna

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Report Number
DRDC-VALCARTIER-CR-2009-400 — Contractor Report
Date of publication
01 Nov 2009
Number of Pages
201
DSTKIM No
CA033630
CANDIS No
533034
Format(s):
Electronic Document(PDF)

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