Airfoil boundary layer calculations using interactive method and en transition prediction technique

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2006

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Mersinligil, Mehmet

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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.

Subject Keywords

Engineering Machinery, Tools, and Implements.

URI

http://etd.lib.metu.edu.tr/upload/12607677/index.pdf
https://hdl.handle.net/11511/16097

Collections

Graduate School of Natural and Applied Sciences, Thesis

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Citation Formats

M. Mersinligil, “Airfoil boundary layer calculations using interactive method and en transition prediction technique,” M.S. - Master of Science, Middle East Technical University, 2006.