A propeller blade design for experimental stall flutter investigations

Abstract

With the development of modern propellers for low acoustic emissions and high performance, the influence of propeller aeroelasticity at low speed, highly loaded conditions may induce stall flutter. Therefore, this must be examined to ensure safe operations. To this end, a propeller blade design has been developed which aims to induce torsional stall flutter in a controlled experimental environment. The design has been developed using rigid and elastic CFD, with the results and process presented within this paper. The main objective is to use the final design and test data for validation of CFD and other aeroelastic methods