Accession Number : ADP004056

Title :   Design of an Airfoil Leading Edge Slat Using an Inverse Aerodynamic Calculation Method,

Corporate Author : NATIONAL AEROSPACE LAB AMSTERDAM (NETHERLANDS)

Personal Author(s) : Egmond,J. A. van ; Berg,B. van den

Report Date : AUG 1984

Pagination or Media Count : 11

Abstract : 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).

Descriptors :   *Aerodynamic control surfaces, Leading edges, Wings, Computer aided design, Aerodynamic configurations, Two dimensional, Incompressible flow, Incompressible flow, Aerodynamic drag, Drag reduction, Wing body configurations, Aircraft noses, Airfoils, High lift, Inversion, Wind tunnel tests, Netherlands

Distribution Statement : APPROVED FOR PUBLIC RELEASE