The aerodynamic and subsequent acoustic effects of nonaxial inflow on wide-chord, advanced high-speed pro- pellers are studied by means of a lifting surface theory. Starting from the flow equations for a perturbed, axially subsonic flow, expressions are derived for the pressure and velocity field of a propeller. By using a representation of Green's function in separated, cylindrical coordinates the boundary condition at the hub is naturally incorporated. Application of the boundary condition at the blade surfaces yields an integral equation for the unknown pressure jump distribution over the blades that is solved numerically.
展开▼
