vortex panel method for airfoil in matlab

Project Description:

select a thick airfoil profile and matching freestream conditions. utilize the vortex panel method to solve for performance characteristics of the upper and lower surfaces. provide plots of lift, pressure, and tangential velocity. use an iterative solving method that you code in matlab, with at least 30 segments for the top and bottom surfaces. you can assume that you have a unit length in the spanwise direction. turn in a report that describes the problem, choice of airfoil, gives plots and a discussion of results, and includes your matlab code as an appendix.
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Project Stats: Edited

Price Type: Fixed

Project Budget: $50 to $100
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