Numerical Study of Flapping-Wing Flow Physics in Nonuniform Freestream Using the High-Order Spectral Difference Method on Dynamic Unstructured Grids

Thumbnail Image

Files

Flapping_Wing_Nonuniform_Flow_AIAA2018.pdf (3.84 MB)

Links to Files

https://arc.aiaa.org/doi/abs/10.2514/6.2018-3087

Permanent Link

https://doi.org/10.2514/6.2018-3087
 http://hdl.handle.net/11603/12766

Collections

UMBC Mechanical Engineering Department
UMBC Faculty Collection
UMBC Student Collection

Author/Creator

Author/Creator ORCID

Date

2018

Type of Work

conference papers and proceedings preprints
Text

Department

Program

Citation of Original Publication

Naresh Poudel and Meilin Yu. "Numerical Study of Flapping-Wing Flow Physics in Nonuniform Freestream Using the High-Order Spectral Difference Method on Dynamic Unstructured Grids", 2018 Fluid Dynamics Conference, AIAA AVIATION Forum, (AIAA 2018-3087), https://doi.org/10.2514/6.2018-3087

Rights

This item is likely protected under Title 17 of the U.S. Copyright Law. Unless on a Creative Commons license, for uses protected by Copyright Law, contact the copyright holder or the author.
© 2019 AIAA

Subjects

impact of nonuniform freestream
aerodynamic performance of a flapping foil
unsteady flow environment
nonuniform freestream
2D low-Mach-number-preconditioned compressible Naiver-Stokes equations on deformable unstructured grids using the high-order spectral difference method
thrust and lift generation

Abstract

In this paper, a numerical study is conducted to understand the impact of nonuniform freestream on the aerodynamic performance of a flapping foil. Specifically, an unsteady flow environment is generated by stationary inline or staggered circular cylinder arrays upstream. A 2D NACA0012 airfoil is then placed at different locations downstream of the cylinder arrays, and oscillates in the nonuniform freestream. Unsteady flows over the flapping foil are numerically simulated by solving the 2D low-Mach-number-preconditioned compressible Naiver-Stokes equations on deformable unstructured grids using the high-order spectral difference method. The flow fields over a pitching airfoil in unsteady flow environments and the corresponding aerodynamic forces are analyzed and compared under different flow conditions. It is observed that the nonuniform freestream can significantly affect the unsteady vortex dynamics of a flapping foil, thus modifying the thrust and lift generation.