Calculations of the Flow over Thick, Conical, Slender Wings with Leading-Edge Separation
نویسندگان
چکیده
The vortex-sheet model of leading-edge separation previously applied to flat-plate delta wings has been applied to thick delta wings in the form of rhombic cones. The simplifications introduced by the use of slender-body theory and an asymptotic treatment for the core of the vortex have been retained. The results show that the vortex sheet leaves the wing tangentially to the lower surface. The calculations reproduce the observed trends with increasing thickness: the vortex core moves upwards and outwards and the circulation and both the linear and non-linear parts of the lift fall off. The quantitative agreement between theory and experiment worsens somewhat as the thickness increases, probably indicating an increase in the influence of the secondary separation.
منابع مشابه
Experimental Investigation of Asymmetry of Vortex Flow Over Single Delta Wings
It is generally believed that, on slender delta wings, there is a critical state at which strong asymmetric vortices are found along the leading edge on the lee-side of the delta wing. These asymmetric vortices can lead to high lateral forces even when slender delta wing is at the zero angle of yaw. Some experimental studies reported recently, cast considerable doubt as to the validity of the a...
متن کاملSome Simple Conical Camber Shapes to produce Low Lift-Dependent Drag on a Slender Delta Wing
ROYAL AIRCRAFT ESTABLISHMENT Some simple conical c~mbcr shapes to produce low lift-depend,cnt drag on a slender delta wing G. G. Brebner This note presents some of the theoretical aerodynamic characteristics of narrow delta wings having flat csntre portions and two types of simple conical camber designed to produce zero load at the leading edge at the design C,.,. Slender wing theory is used in...
متن کاملExperimental Investigation of the Positions of the Leadir/g-Edge Vortices above Slender Delta Wings with Various Rhombic Cross-Sections in Subsonic Conical Flow
The positions of the centres of the leading-edge vortices above four slender wings have been located at several angles of incidence using a Kiel tube probe, and measured using a mutual inductance method of &stance measurement. This method was developed for use in this experiment to provide accurate information about the position of a probe in the flow field by measuring the mutual inductances b...
متن کاملStability of Symmetric and Asymmetric Vortex Pairs over Slender Conical Wings and Bodies
Theoretical analyses are presented for the stability of symmetric and asymmetric vortex pairs over slender conical wings and bodies under small perturbations in an inviscid incompressible flow at high angles of attack and sideslip. The three-dimensional problem of a pair of vortices over slender conical wings and bodies is reduced to a problem in two dimensions by using the conical flow assumpt...
متن کامل