Accession Number : ADA138530
Title : Leading Edge Devices, Slats on Swept-Back Slender Wings with Flow Separation.
Descriptive Note : Final rept. 1 May 79-30 Jun 80,
Corporate Author : BRISTOL UNIV (ENGLAND) DEPT OF AERONAUTICAL ENGINEERING
Personal Author(s) : Nangia,R K
PDF Url : ADA138530
Report Date : Jun 1980
Pagination or Media Count : 156
Abstract : Leading edge devices and slats are applicable to high speed wing planforms with high sweepback or strakes. This includes aircraft with transonic maneuverability capability and supersonic cruise vehicles. A theoretical approach within the framework of conical slender wing theory has been presented that deals with thin delta wings with leading edge slats including flow separations. Specimen calculations suggest that benefits in performance (lift/drag) are strongly dependent on the flow conditions prevailing at the edges of the configuration (i.e. whether the flow is attached or separated). In general lift-drag benefits of 10%-40% are obtainable with suitable configurations. These benefits are of the same order as those indicated by experiments.
Descriptors : *Delta wings, *Leading edge flaps, *Flow separation, Lift to drag ratio, High lift, Leading edges, Aerodynamic configurations, Slender bodies, Equations of motion, Supersonic aircraft
Subject Categories : Aircraft
Distribution Statement : APPROVED FOR PUBLIC RELEASE