Research On The Interaction Flowfield Of Compound High-Speed Helicopter Rotor/Fuselage/Auxiliary Propulsor

The flowfield interaction simulation of the compound high-speed helicopter is a challenging and significant subject in rotorcraft aerodynamics. Combining the momentum resource model, this thesis established a numerical computation method of rotor/fuselage/ auxiliary propulsor flowfield interaction based on Navier-Stokes equations. A deep research was conducted about rotor/fuselage/ flowfield interaction by applying this method in different flight regimes. The main work is as follows:In this thesis, the current state of research was introduced firstly, and the deficiencies of existing research were pointed out. The necessity and significance of flowfield research and the method adopted in this thesis were presented.In the second chapter, considering the flowfield and movement characteristics of the compound high-speed helicopter, a computation model involved rigid coaxial rotor and auxiliary propulsor was established, and the grid suitable for flowfiled interaction computation was given. Meanwhile, the results of isolated rotor were compared with available experimental data to validate the effectiveness of presented model.The third chapter of this thesis was the research about rotor/fuselage aerodynamic interaction of the compound high-speed helicopter. The flowfiled interaction characteristics of hover and forward flight were calculated, separately. Besides, the influences of different rotor installation height and upper and lower rotor pitch on flowfield interaction were investigated.The fourth chapter was aerodynamic interaction research. Flowfiled characteristics of isolated auxiliary propulsor were calculated firstly. On this basis, the aerodynamics influences of rigid coaxial rotor on auxiliary propulsor in different flight speed were analyzed emphatically. The flowfiled interaction of the propeller pull layout were investigated, which were of actual guding significance to high speed configuration.In the fifth chapter, applying the established numerical simulation method, the aerodynamic interaction of the whole helicopter was calculated and analyzed in different flight speed and collective pitch. Some meaningful conclusions were obtained.Finally, in the last chapter, the main work of this thesis was summarized and the outlook of further study was presented.