CFD investigation of the aerodynamic characteristics of the autogyro with a double tail stabilizer

Abstract

Abstract Drag, lift and pitching moment were calculated for the tested aircraft sectioned into the fuselage and stabilizer. The analysis also covered the pressure distribution on the surface of this aircraft and on its symmetry plane. The values of the analysed forces and moments on individual parts of the stabilizer for the defined angles of attack were also obtained. The conducted analysis is a preliminary aerodynamic study of a new type of aircraft which is a combination of a gyroplane and a multi-rotor. The obtained results allow the assessment of the aerodynamic performance of the aircraft with a double tail stabilizer and constitute the basis for further optimisation studies.