Computational Study on the Effects of Unsteady Freestream on an Airfoil Performance at Low Reynolds Numbers
| dc.contributor.author | Poudel, Naresh | |
| dc.contributor.author | Yu, Meilin | |
| dc.contributor.author | Hrynuk, John T. | |
| dc.date.accessioned | 2021-02-16T17:18:48Z | |
| dc.date.available | 2021-02-16T17:18:48Z | |
| dc.date.issued | 2021-01-04 | |
| dc.description | AIAA Scitech 2021 Forum, 11–15 , 19–21 January 2021, VIRTUAL EVENT | en_US |
| dc.description.abstract | Computational studies of the response of a NACA0012 airfoil at varying angles of attack (α) to freestream turbulence at low Reynolds numbers (i.e., 12,000 based on the airfoil chord length) are conducted in this work. The unsteady freestream is generated by placing an array of circular cylinders upstream of the airfoil. The presence of moderate freestream turbulence (~5%) affected the formation of laminar separation bubbles near the leading edge of the airfoil, which has significant impacts on the aerodynamic performance. The study was able to recreate the maximum lift coefficient of the airfoil in unsteady freestream turbulence observed in experiments, which is higher than that for the airfoil in a uniform freestream. In general, the present numerical results agree reasonably well with those from experimental studies. This work also demonstrates that three-dimensional (3D) simulations with high-order accurate numerical methods predict the lift coefficient more accurately than lower dimension (i.e., 2D) or lower order 3D methods. | en_US |
| dc.description.sponsorship | This research was supported in part by an appointment to the Science Education and Workforce Development Programs at Oak Ridge National Laboratory, administered by ORISE through the U.S. Department of Energy Oak Ridge Institute for Science and Education. Research was partially supported by the Combat Capabilities Development Command - Army Research Laboratory under CRADA 14-054-003. The views and conclusions in this document are those of the authors and should not be interpreted as representing the official policies, either expressed or implied, of the Army Research Laboratory or the U.S. Government. The U.S. Government is authorized to reproduce and distribute reprints for Government purposes notwithstanding any copyright notation herein. The hardware used in the computational studies is part of the UMBC High Performance Computing Facility (HPCF). The facility is supported by the U.S. National Science Foundation through the MRI program (grant nos. CNS-0821258, CNS-1228778, and OAC-1726023) and the SCREMS program (grant no. DMS-0821311), with additional substantial support from the University of Maryland, Baltimore County (UMBC). | en_US |
| dc.description.uri | https://arc.aiaa.org/doi/10.2514/6.2021-0965 | en_US |
| dc.format.extent | 15 pages | en_US |
| dc.genre | conference papaers and proceedings postprints | en_US |
| dc.identifier | doi:10.13016/m2s7xq-vbx2 | |
| dc.identifier.citation | Naresh Poudel, Meilin Yu and John T. Hrynuk, Computational Study on the Effects of Unsteady Freestream on an Airfoil Performance at Low Reynolds Numbers, AIAA Scitech 2021 Forum, DOI: https://doi.org/10.2514/6.2021-0965 | en_US |
| dc.identifier.uri | https://doi.org/10.2514/6.2021-0965 | |
| dc.identifier.uri | http://hdl.handle.net/11603/21036 | |
| dc.language.iso | en_US | en_US |
| dc.publisher | American Institute of Aeronautics and Astronautics | en_US |
| dc.relation.isAvailableAt | The University of Maryland, Baltimore County (UMBC) | |
| dc.relation.ispartof | UMBC Mechanical Engineering Department Collection | |
| dc.relation.ispartof | UMBC Student Collection | |
| dc.relation.ispartof | UMBC Faculty Collection | |
| dc.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. | |
| dc.subject | UMBC High Performance Computing Facility (HPCF) | |
| dc.title | Computational Study on the Effects of Unsteady Freestream on an Airfoil Performance at Low Reynolds Numbers | en_US |
| dc.type | Text | en_US |