Design of an Airfoil Leading Edge Slat Using an Inverse Aerodynamic Calculation Method,
NATIONAL AEROSPACE LAB AMSTERDAM (NETHERLANDS)
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A two-element airfoil design study was performed with the objective of evaluating the capabilities of a computer program system for the aerodynamic design of multi-element airfoils. In the present study a two dimensional wing-slat combination, tested earlier in the wind tunnel, was selected as the starting configuration. From these tests, the takeoff condition for this configuration appeared to suffer from an early turbulent boundary layer separation on the main wing upper surface resulting in high drag values. To improve the drag characteristics, a new slat-wing configuration was designed. The design focussed on the main wing nose geometry at the slat-wing intersection. Both, the original and the new slat-wing configuration have been tested in the NLR low speed wind tunnel LST 3 x 2 at Mach no. 0.19 and Rec 3.1 million. The tests showed a substantial improvement in the drag characteristics for the new configuration and unchanged maximum lift properties in takeoff condition.