A two-dimensional fluid-structure coupling algorithm for the interaction of high-speed flows with open shells
Name
56570723-MIT.pdf
Description
Full printable version
Size
7.53 MB
Format
Adobe PDF
Checksum (MD5)
80166bd790ed4baa0a65a3af96e46c7f
Author(s)
Tam, Daniel See Wai, 1980-
Advisor(s)
Raúl Radovitzky.
Date Issued
2004
Publisher
Massachusetts Institute of Technology
Abstract
The design of future light aerospace structures will require numerical tools to accurately describe the strongly coupled dynamics of the interactions between a light structure and a flow surrounding it. Specific examples include inflatable structures and parachutes used as deceleration devices during planet entry. In this work, an algorithm for simulating the solid-fluid interactions of a highly-deformable open shell structure and a compressible fluid flow is presented. The main objective is to extend the algorithm previously presented by the authors to the case of open shell structures immersed in a fluid. For simplicity, we restrict our attention to the two-dimensional case. The computational strategy is based on combining an Eulerian finite volume formulation for the fluid and a Lagrangian formulation for the structural response. The coupling between the fluid and the solid response is achieved via a novel approach based on extrapolation and velocity reconstruction aided by level sets. The accuracy of the proposed approach is verified against exact solutions of supersonic flow past a rigid flat plate. The numerical results reproduce all the details of the flow field, including the-very important-forces on the structure. The versatility of the proposed coupling algorithm is demonstrated in simulations of supersonic flow past a highly-deformable infinite plate.
Description
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2004.
Includes bibliographical references (p. 89-94).
Subjects
Aeronautics and Astronautics.
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Terms of Use
M.I.T. theses are protected by copyright. They may be viewed from this source for any purpose, but reproduction or distribution in any format is prohibited without written permission. See provided URL for inquiries about permission.
Persistent DSpace Link
