Leading Edge stall ?

07 February 2018 0 308 Report

Attached is a figure showing the pressure coefficient distribution over the suction surface for two delta winglets(named surface 1 and surface 2) at a very high angle of attack of 45. The leading edge of the surface 2 is blunt(in the attached jpg).

Looking at the CP distribution, what obervations and conclusions can one make regarding the difference is separation, pressure drag and vortex structure of the two winglets ?

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