A vortex point method for calculating inviscid incompressible flows around rotary wings
Abstract
An integral method is presented for calculating incompressible inviscid unsteady flow around thin bodies in arbitrary motion, i.e., rotor blades in motion with respect to one another. Because an integral method is used, discretization is limited to the solid boundaries and the vortices. Boundary conditions are treated in terms of equation for the slipstream on the walls, the vorticity vector, a volume integral for the vorticity and a firstorder Fredholm integral. The Helmholtz equation governs the evolution of vorticity, which forms a sheet of doublets. The pressure jumps on the blades are covered by the unsteady Bernoulli equation. Applications of the method to helicopter rotors, medium and highaspect ratio propellers and lowaspect ratio nautical propellers are demonstrated.
 Publication:

La Recherche Aerospatiale
 Pub Date:
 May 1985
 Bibcode:
 1985ReAeB.........C
 Keywords:

 Computational Fluid Dynamics;
 Incompressible Flow;
 Inviscid Flow;
 Rotary Wings;
 Unsteady Flow;
 Vortices;
 Aspect Ratio;
 Flow Theory;
 Helmholtz Vorticity Equation;
 Kinematics;
 Propeller Slipstreams;
 Propellers;
 Three Dimensional Flow;
 Fluid Mechanics and Heat Transfer