
Accession Number : AD0251131
Title : AN ANALYTICAL STUDY OF THE LOWSPEED AERODYNAMICS OF STRAIGHT AND SWEPT WINGS WITH FLOW SEPARATION
Corporate Author : ITEK CORP PALO ALTO CA VIDYA DIV
Personal Author(s) : SACKS, ALVIN H. ; NIELSEN, JACK N.
Report Date : 31 JAN 1961
Pagination or Media Count : 1
Abstract : A mathematical theory is developed for the lowspeed aerodynamics of rectangular wings with sideedge separation. The assumed vortex system consists of a lifting line with its associated trailing sheet (lying in the plane of t e wing) and a separated vortex sheet from each side edge with an associated bound vortex system in the wing. The Kutta condition is satisfied along the side edges, and the boundary condition of no flow through the wing is satisfied along a selected control line for all spanwise points by means of Fourier analysis. The resulting theory includes the classical liftingline theory of Prandtl and provides a means of calculating the downwash anywhere in the plane of the lifting line. Calculations were made of the normal force, span loading, and center e for a rectangular wing of aspect ratio two, and comparisons with experiment are presented. The analysis is extended to wings with sweptback leading edges (and straight trailing edges) by representing the actual wing as a system of elementary rectangular wings of varying aspect ratio. For extremely large sweep angles, a method is presented for calculating the normal force on general slender configurations with leadingedge separation using the crossflow drag concept. (Authof pressure for a rectangular wing of aspect ratio two, and comparisons with experiment are presented. The analysis is extended to wings with sweptback leading edges (and straight trailing edges) by representing the actual wing as a system of elementary rectangular wings of varying aspect ratio. For extremely large sweep angles, a method is presented for calculating the normal force on general slender configurations with leadingedge separation using the crossflow drag concept. (Author)
Descriptors : *AERODYNAMIC CHARACTERISTICS, *WINGS, ASPECT RATIO, DELTA WINGS, GAS FLOW, MATHEMATICAL ANALYSIS, SEPARATION, SWEPTBACK WINGS, VORTICES.
Distribution Statement : APPROVED FOR PUBLIC RELEASE