2026-09-18T21:47:35Zhttps://dspace.mit.edu/server/oai/requestoai:dspace.mit.edu:1721.1/430782022-01-13T07:54:11Zcom_1721.1_7582com_1721.1_7581col_1721.1_131023
David L. Darmofal.
Modisette, James M
Massachusetts Institute of Technology. Dept. of Aeronautics and Astronautics.
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
2008-11-07T18:59:38Z
2008-11-07T18:59:38Z
2008
2008
http://hdl.handle.net/1721.1/43078
244303143
Thesis (S.M.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 2008.
Includes bibliographical references (p. 69-73).
A high-order discontinuous Galerkin finite element discretization and output-based adaptation scheme for the compressible Euler equations are presented and applied to an isolated rotor in hover. A simplex cut-cell mesh generation technique is used to support robust and autonomous creation of higher-order meshes. The calculations are performed using a parallel implementation of the DG discretization and the results are compared to experimental data. As accurate simulation of rotorcraft wakes and blade-vortex interactions continues to be a challenge, the output-based adaptation scheme is used with thrust as the output of interest to refine the mesh. The result is a solution with less than three million degrees of freedom that is capable of preserving a rotor tip vortex for three and a half revolutions.
by James M. Modisette.
S.M.
73 p.
eng
Massachusetts Institute of Technology
M.I.T. theses are protected by
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http://dspace.mit.edu/handle/1721.1/7582
Aeronautics and Astronautics.
An output-based adaptive and high-order method for a rotor in hover
Thesis
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<Abstract>A high-order discontinuous Galerkin finite element discretization and output-based adaptation scheme for the compressible Euler equations are presented and applied to an isolated rotor in hover. A simplex cut-cell mesh generation technique is used to support robust and autonomous creation of higher-order meshes. The calculations are performed using a parallel implementation of the DG discretization and the results are compared to experimental data. As accurate simulation of rotorcraft wakes and blade-vortex interactions continues to be a challenge, the output-based adaptation scheme is used with thrust as the output of interest to refine the mesh. The result is a solution with less than three million degrees of freedom that is capable of preserving a rotor tip vortex for three and a half revolutions.</Abstract>
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