A Strongly-coupled Non-parametric Integral Boundary Layer Method for Aerodynamic Analysis with Free Transition
Name
scitech2019_manuscript.pdf
Description
Accepted version
Size
1006.71 KB
Format
Adobe PDF
Checksum (MD5)
eacb93e208e9c3a36f60ecccb6b8d696
Author(s)
Zhang, Shun
Drela, Mark
Galbraith, Marshall C.
Allmaras, Steven R.
Darmofal, David L.
Date Issued
January 2019
Publisher
American Institute of Aeronautics and Astronautics (AIAA)
Citation
Zhang, Shun, Drela, Mark, Galbraith, Marshall C., Allmaras, Steven R. and Darmofal, David L. 2019. "A Strongly-coupled Non-parametric Integral Boundary Layer Method for Aerodynamic Analysis with Free Transition."
Version
Author's final manuscript
Abstract
© 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. The integral boundary layer (IBL) method with viscous-inviscid coupling is an effective tool for rapid aerodynamic design and analysis. However, existing IBL methods remain to be extended to general three-dimensional (3D) configurations. To this end, previous work proposed an IBL formulation using the discontinuous Galerkin (DG) finite element method (FEM) with strong viscous-inviscid coupling, which is non-parametric in the sense that the aerodynamic shape is does not have to be explicitly parametrized by curvilinear coordinates. The current work builds on that strongly-coupled non-parametric IBL formulation, and further develops numerical discretization methods to enable flow transition modeling. Both a cut-cell-based fitted transition approach and a simple captured transition approach are presented and compared. In solving the nonlinear system of equations arising from free-transition problems, a strongly-coupled global Newton solver is adopted and augmented for solution robustness. Numerical results demonstrate favorable accuracy and robustness of the cut-cell fitted transition method compared to the captured transition methods. On the other hand, the captured transition approach allows for a more straightforward numerical implementation, but requires further improvement to achieve comparable reliability for aerodynamic analysis with free transition.
MIT Department
Massachusetts Institute of Technology. Department of Aeronautics and Astronautics
Terms of Use
Creative Commons Attribution-Noncommercial-Share Alike
Persistent DSpace Link
DOI of Published Version
https://doi.org/10.2514/6.2019-1154
