Volume 34 Issue 12
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ZHANG Juhui, CHEN Renliang, KONG Weihong. Numerical simulation for flow field of helicopters based on WENO-piecewise linear scheme[J]. Journal of Aerospace Power, 2019, 34(12): 2589-2598. doi: 10.13224/j.cnki.jasp.2019.12.007
Citation: ZHANG Juhui, CHEN Renliang, KONG Weihong. Numerical simulation for flow field of helicopters based on WENO-piecewise linear scheme[J]. Journal of Aerospace Power, 2019, 34(12): 2589-2598. doi: 10.13224/j.cnki.jasp.2019.12.007
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Numerical simulation for flow field of helicopters based on WENO-piecewise linear scheme

doi: 10.13224/j.cnki.jasp.2019.12.007

  • National Key Laboratory of Science and Technology on Rotorcraft Aeromechanics,College of Aerospace Engineering,Nanjing University of Aeronautics and Astronautics,Nanjing,210016,China

  • Received Date: 2019-06-22
  • Publish Date: 2019-12-28
    Abstract
  • A high-precision CFD method based on WENO(weighted essentially non-oscillatory)-piecewise linear scheme was established for numerical simulation on the rotor/fuselage aerodynamics interaction flow field. And it was suitable for the CFD solver of cell-centered scheme. The pressure coefficient on the surface of the fuselage of different rotor/fuselage model examples in forward flight was calculated by the method, and the calculation results were in good agreement with the experimental results, verifying the effectiveness of the calculation method. Then, the method was extended to simulate the flow field of X3 compound high-speed helicopter rotor/wing/propeller model in hover, and the flow field was compared with flow field of single rotor and rotor/wing model in hover. The results showed that the wing acted as a retarder on the downwash of rotor, causing the irregular flow under the wing. Furthermore, the slipstream of propeller and the downwash of rotor interfered with each other to produce a certain deflection, and the speed of downwash was faster than the speed of slipstream, the downward deflection of propeller slipstream was significant.

     

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