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  • Department of Fluid Mechanics
    Department of Aircraft Design Engineering
    Department of Aeronautical Structure Engineering
    Department of Fluid Mechanics
    Department of Integrated Technology and Control Engineering
    Department of Civil Aviation Engineering
    Current Location: English > Departments > Department of Fluid Mechanics > Content
    Department of Fluid Mechanics
    2012-02-16   審核人:

    The Department of Fluid Mechanics has nearly 60 faculty members, including 14 professors and 16 associate professors. There are 13 wind tunnels in total in the department, including 5 scientific research wind tunnels and 7 teaching wind tunnels. Two of them are larger, one is the NF-3 low-speed wind tunnel, and the other is the NF-6 high-speed wind tunnel.

    The research activities in the department include CFD Applications, Flow control, Design of Airfoils and Wings, and aeroelasticity.

    The activities of CFD mainly focus on the industry application. Most of the financial supports come from the aeronautical and astronautical industries, as well as the fund from natural science foundations. Different types of codes have been developed in-house, such as codes based on the panel method, full potential equations, and Euler/NS Eqs. Many up-to-date turbulence models have been adopted for the simulation of viscous effects.

    The aerodynamic design includes design of engineering application and the study of design approaches. The design approaches of airfoils and wings are mainly adjoint method and response surface methodology.

    The research work on flow control includes plasma flow control, vortex generator, fluidic vector thrusting and micro zero-mass-flux jet.

    The research work on aeroacoustics includes aeroacoustic noise prediction of subsonic and transonic helicopter rotors in hover and in forward flight, and preliminary study on airframe noise prediction based on CFD simulation.

    The research work on aeroelasticity include static response of wings, aircraft flutter, buzz of control surface, ROM (Reduced Order Model) of unsteady aerodynamic loads based on CFD, active control on the transonic flutter suppression.

    Main research fields

    Theoretical aerodynamic

    CFD

    Aerodynamic design

    Experimental aerodynamic

    Flow control

    Aeroacoustics

    Aeroelastics

    Famous professors

     

     

    Professor Gao Zhenghong

    Professor Ye Zhengyin

     

     

     

    Professor Zhang Binqian

    Professor Cai Jinsheng

     

     

     

    Professor Li Dong

    Professor Song Wenping

     

     

     

    Professor Bai Cunru

    Professor Gao Chao

     

     

     

    Professor Zhang Zhengke

    Professor Zhong Chengwen

     

     

     

    Professor Liu Feng

    Facilities

    NF-3 low-speed wind tunnel is a direct flow type wind tunnel, established in 1988. The wind tunnel can carry out force test for complete model, pressure distribution measurement of model surface, and half model test, and test for model propeller and airplane model with propeller, etc. NF-6 wind tunnel With 2 changeable test sections: 2-D test section, 3-D test section. Ma=0.31.2,Remax=1.5×107 .

     

     

     

    NF-3 low speed wind tunnel

    NF-6 transonic wind tunnel

     

    Main research results

    1.    Theoretical aerodynamics

    Stability prediction vortices

     

    Vortex instability prediction over a wing-body combination

     

     

    Pressure contours for 2D models

    2.    Computational fluid dynamics

    Meshing methods

    Computational methods

     

     

    Aerodynamic design and analysis for transport airplane

    Airfoil and Wing Design for Flying Wing UAV

     

     

     

    Aerodynamic Design of Propeller

    Propeller Slipstream Effect Analysis for UAV

     

    Turbulence flow simulation by IDDES method

     

    Numerical Analysis of Flowfield for Helicopter Rotors

     

    The flow around a fighter at high angle of attack and Mach number contour of hypersonic base flow computed by SAS and LES

     

    Coherent structures predicted by implicit LES for the incompressible flow over a shallow bump

     

    Computational Schlieren image of the high subsonic flow over a deep cavity

    3.    Aerodynamic design methodologies

    Optimization methods

     

    Design result of airfoil at transonic condition (the shock wave moves backward and is weaker after optimization)

     

    Inverse design of a transonic airfoil (from NACA 0012 to RAE 2822)

     

    Design of transonic wing (After design the shock waves is removed)

    4.    Aeroelastic analysis

     

    Cropped delta wing model shapes

     

    Meshes distribution on the upper surface and lower surface AD Slice of the body meshes at x=0.6

     

    Slices of pressures at different locations

     

    Aeroelastic response of wing 

    5. Aeroacoustics

     

    Aeroacoustic noise prediction using CFD/FW-H methods for helicopter rotors, wind turbine airfoils and tandem cylinders

     

    6. Experimental aerodynamics

     

    Instantaneous laser-sheet image at x/c0 = 0.54, α = 29.09 deg, U∞ = 4.5 m/s for Wing alone (Left), Wing + 0.75s fin (Middle), Wing + 1.50s fin (Right).

     

    Time-averaged velocity distribution based on PIV technique of vortex over a conical cone, α = 45 deg.

     

    Research in 3-D boundary layer transition mechanism

    7. Flow control

    VGS (vortex generator systems)

    Plasma flow control

    Separation control by synthetic jet

     

    VGS design for separation control

     

    Ensemble-averaged PIV contours of AC DBD plasma duty cycle control, (Left) t  = 1%, (Middle) t  = 50%, (Right) t  = 99%

     

    Time-averaged local side force vs. reduced frequency by using AC plasma DBD actuation, α = 45°, U∞ = 5 m/s.

     

    Pressure distributions under steady NS plasma DBD actuation , Vmax=14.6 kV, α = 45°, U∞ = 42m/s.

     

    Wave structures induced by NSDBD

     

    Predicted wave positions compared with experimental data

     

    Coherent structures without/with control indicated by iso-value of Q at low Reynolds number

     

    Vorticity contours without/with control at high Reynolds number

     

    Synthetic jet flow control

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    Email: zheng2014@nwpu.edu.cn
    Copyrights 2019 School of Aeronautics Technical support: Zhao YouGuo
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