The aerodynamic effects of fixing a serrated strip near the leading edge, forward of the stagnation point at high incidence, was investigated using 2 airfoil models, both of 254 mm chord, but of different sections. The aerodynamic force and moment coefficients were determined for the basic and modified airfoils. The devices tested improve the maximum lift of a NACA 65(1)-212 section by up to 16% without drag penalties. However, they degrade the performance of an NLF(1)-0416 section. All leading-edge devices tested generate vortices which stream around the airfoil leading edge and over the suction surface. On the NACA airfoil only, these vortices reduce the extent of local separation near the leading edge and re-energize the turbulent boundary layer, thus delaying the onset of trailing edge separation.
Aerodynamic Effects of a Serrated Strip Near the Leading Edge of an Airfoil
1986
139 pages
Report
No indication
English
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