Transactions of Nanjing University of Aeronautics & Astronautics
Low Dissipation Simulation for Vortex Flowfield of Rotor in Hover Based upon Discontinuous Galerkin Method
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Abstract:
The discontinuous Galerkin（DG） method is established and innovatively conducted on accurately simulating the evolution of blade-tip vortex and the aerodynamic characteristics of helicopter rotor. Firstly， the Reynolds-Averaged Navier-Stokes（RANS） equations in rotating reference frame are employed， and the embedded grid system is developed with the finite volume method （FVM） and the DG method conducted on the blade grid and background grid respectively. Besides， the Harten-Lax-Van Leer contact （HLLC） scheme with high-resolution and low-dissipation is employed for spatial discretization， and the explicit third-order Runge-Kutta scheme is used to accomplish the temporal discretization. Secondly， the aerodynamic characteristics and the evolution of blade-tip vortex for Caradonna-Tung rotor are simulated by the established CFD method， and the numerical results are in good agreement with experimental data， which well validates the accuracy of the DG method and shows the advantages of DG method on capturing the detailed blade-tip vortex compared with the FVM method. Finally， the evolution of tip vortex at different blade tip Mach numbers and collective pitches is discussed.
Keywords:
blade-tip vortex ; discontinuous Galerkin （DG） method ; Navier-Stokes（N-S）equations ; aerodynamic characteristics ; helicopter rotor
Project Supported:
This work was supported by the National Natural Science Foundation of China （Nos.12072156， 12032012）， the Foundation of Rotor Aerodynamic Key Laboratory （No.RAL20190102）， and the Priority Academic Program Development Project of Jiangsu Higher Education Institutions （PAPD）.
Clc Number:
V211.52
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