In this thesis, the Leishman-Beddoes method of determining airloads for
an airfoil undergoing dynamic stall is studied over a range of Mach numbers. To
validate the method for conditions where little experimental data is available, a
computational fluid dynamics solver is utilized to provide airload predictions for
comparison to the Leishman-Beddoes results.
It is found that even for high Mach numbers the Leishman-Beddoes
method provides reliable predictions for lift coefficient. However, at the higher
Mach numbers pitching moment is sometimes overpredicted at high angle of
attack. This is seemingly due to an inability to accurately determine the center of
pressure in the high speed unsteady flow environment.
| Identifer | oai:union.ndltd.org:GATECH/oai:smartech.gatech.edu:1853/33866 |
| Date | 26 January 2010 |
| Creators | Clark, Brian |
| Publisher | Georgia Institute of Technology |
| Source Sets | Georgia Tech Electronic Thesis and Dissertation Archive |
| Detected Language | English |
| Type | Thesis |
Page generated in 0.002 seconds