ADVANCED PROPELLER PERFORMANCE CALCULATION BY A LIFTING SURFACE METHOD

The application of a lifting surface theory to compute the aerodynamics of advanced propellers is studied. Starting from the inviscid, compressible flow equations for a perturbed, axially subsonic flow, expressions are derived for the velocity field of a propeller. By using a representation of Green's function in separated, cylindrical coordinates, the radial boundary condition at the hub is naturally incorporated in the velocity field. Application of the boundary condition at the blade surfaces yields an integral equation for the unknown pressure jump distribution over the blades. A Galerkin projection transforms this integral equation into a set of linear equations, which is solved numerically. Comparison with experimental data shows that the gradients of thrust and power coefficients vs the advance ratio at the windmilling point are accurately predicted. By taking into account some higher-order effects in the geometry description of the blades, and by application of the so-called leading-edge suction analogy, a good agreement between theory and experiment is maintained up to high aerodynamic loading.

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