Boundary layer calculations are performed around an airfoil and its wake. Smith-van Ingen
transition prediction method is employed to find the transition from laminar to turbulent
flow. First, potential flow around the airfoil is solved with the Hess-Smith panel method.
The resulting velocity distribution is input to the boundary layer equations in order to find
a so called blowing velocity distribution. The output of the boundary layer equations are
also used to compute the location of onset of transition using the Smith-van Ingen en
transition prediction method. The obtained blowing velocity distribution is fed back to the
panel method to find a velocity distribution which includes the effects of viscosity. The
procedure described is repeated until convergence is observed. A computer program is
developed using the theory. Results obtained are in good accord with measurements
| Identifer | oai:union.ndltd.org:METU/oai:etd.lib.metu.edu.tr:http://etd.lib.metu.edu.tr/upload/12607677/index.pdf |
| Date | 01 September 2006 |
| Creators | Mersinligil, Mehmet |
| Contributors | Ozgen, Serkan |
| Publisher | METU |
| Source Sets | Middle East Technical Univ. |
| Language | English |
| Detected Language | English |
| Type | M.S. Thesis |
| Format | text/pdf |
| Rights | To liberate the content for public access |
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