Abstract
Smith's method of calculating flow with leading separation on plane delta wings in subsonic flow is extended to the case of spanwise cambered delta wings, through the use of a system of conformal transformations. A numerical procedure to develop the required transformation is described. Using the transformations, a study of the effect of spanwise camber on the flow characteristics such as vortex core location and strength, sheet shape, pressure distribution, and normal force is made on a conically cambered delta wing. It is found that, at a given incidence measured from the respective zero lift angle, the core vortex on the cambered wing lies more outboard towards the leading edge and closer to the wing surface than that on the plane wing. Core and sheet vortex strengths of the cambered wing are less than those of plane wings. Significant changes in sheet shape and the location and magnitude of suction peaks are observed as a function of spanwise camber. However, with increase in incidence, the camber wing characteristics approach those of the plane wing, indicating the diminishing influence of spanwise camber on the flow details at large incidence. Since the theoretical flow model is based on the assumption of conical flow in the separated flow field and slender wing theory for attached flow, the method is applicable in the forward region near the apex of low aspect ratio wings.
Published Version
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call