No abstract

A vortex model of a flapping aerofoil with LE detached vortex sheet is presented. A system of equations, one integral that imposes the boundary condition and other describing the motion of the wakes and vorticity conservation are written. To these one must add the Kutta-like condition and the initial conditions for the wakes. A numerical solution was given that consists of a modified Glauert method in connection with vortex range wake models with finite cores. Mathcad worksheets were written to obtain numerical values and diagrams.

The goal of the paper is to propose a new type of ornithopter that avoids the mechanical difficulties of a flapping system. It uses a modified design of a cycloidal propulsor. The modification regards the special setting of the wings that is intended to help the formation of a stable leading edge vortex (LEV).It is known that the LEV is the main feature that allows the insects to achieve the necessary lift to fly.

In the sixth part of this series, we continue our study started in the previous article, i.e., we present the basis of the method for calculating the unsteady airforces on oscillating non-lifting bodies. The method proposed here is a panel one. As it is proved in the previous paper, the potential and velocity induced by a constant source planar panel is composed of two kinds of terms: some of themthe steady terms, can be expressed by the elementary functions; other terms-the unsteady termscannot and should be calculated numerically. The present paper illustrates how the method proposed here can be used in conjunction with the preceding results.