Investigation Of The Aerodynamic Interaction Between Rotor/Fuselage/Horizontal Of Helicopter

Based upon the momentum-source model, a N-S equation solution method for analyzing the aerodynamic interactions between rotor/fuselage/horizontal of helicopter has been developed in this thesis. By the method, aerodynamic interactions under various of flight speeds have been calculated, and the results have been analyzed. The major research work in the thesis is as follows:As the precondition and background of the research, the development of CFD methods in the analyse of helicopter rotor/fuselage/horizontal is introduced briefly, and it is pointed out the CFD method is important for the research of helicopter rotor/fuselage/horizontal interactions.The geometry model and math model for calculating the aerodynamic interaction between rotor/fuselage/horizontal of helicopter has been developed, and a hybrid mesh generation approach is given by considering the requirements from the momentum-source method, in term of the blade aerodynamic characteristics, the blade will be simulated by the momentum-source method. The method for analyzing the aerodynamic interaction between rotor/fuselage/horizontal of helicopter has been developed.The calculate results are compared with available experimental data. Then, by the method, aerodynamic interactions under various of flight speeds have been calculated, and the results have been analyzed and some meaningful results are obtained.