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Numerical Simulation of Bionic Wing for Drag Reduction Lihong Zhang 1, a, Weijie Li 2,b and Jixin Yin 3,c 1 Basic Course Department of Aviation University of Air Force,Changchun,China 2 Scientific research department of Aviation University of Air Force,Changchun,China 3 Aviation Theory Department of Aviation University of Air Force,Changchun,China azhlhjj@163.com, b58116492@qq.com, c25010511@qq.com Keywords: Airfoil; Computational fluid dynamics; Bionic; Drag reduction Abstract: According to the presence of the rounded protuberances or tubercles located on the leading edge, a similar leading edge of humpback whale pectoral fin with the “paraganglioma” has been made on the leading edge of NACA63-210 wing, an bionic NACA63-210 airfoil is designed with convex-concaved leading edges, and the 3-dimensional flows around the bionic wing are simulated for the drag reduction purpose.
The 3-D Numerical Simulations for the Standard and Bionic Wing The chord length of standard wing is 0.2m and wingspan is 0.4m( see Fig. 1), the wingspan of bionic wing is 0.4m, the maximum chord length is at the point 0.12m and 0.28m of the wingspan, which is 0.11m; the minimum chord length is at the point 0.04m, 0.2m and 0.36m of the wingspan, which is 0.09m(see Fig. 2).

The simulation is carried out and performance parameters like power coefficient and torque coefficient are calculated.
The authors carried out simulations and compared the results with numerically analysed Savonius model.
A two dimensional unsteady simulation is carried out over the rotors.The 2D model is generated by GAMBIT 2.4.
[8] Khandakar Niaz Morshed, Mosfequr Rahman, Gustavo Molina and Mahbub Ahmed, Wind tunnel testing and numerical simulation on aerodynamic performance of a three-bladed Savonius wind turbine, International Journal of Energy and Environmental Engineering 4 (2013)18
Steady and rotating computational fluid dynamics simulations of a novel vertical axis wind turbine for small-scale power generation, Renewable Energy 41 (2012) 171-179

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Separation Simulation of lubricant with cold intermediary is accomplished with the computational fluid dynamics software to obtain some parameters affecting the separation efficiency.
The structure parameters taken into account in simulation are cold intermediary exit diameter D1 and lubricant going-back diameter D2.
Through the set-up of hydrodynamics simulation testing plan and reasonably arranging parameters, the optimum value would be got finally.
The numerical simulation research of effects of interior structures deformation on characteristic of cyclone separator(in Chinese)[D].

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Aiming to make a comparative study between the filtering hydrocyclone and the conventional one, we conducted numerical bi-dimensional simulations [9] in the commercial software Fluent with an average of 100000 rectangular computational cells [10].
The fluid dynamic simulations also proved such fact and they showed that the filtration is capable of decreasing the rotational movement of the fluid in the conical region of the hydrocyclone, in agreement with the profile of swirl velocity showed in Fig. 3.
Conclusions According to the experimental data and the fluid dynamic simulations, we were able to conclude, in the comparative study between the hydrocyclones FH and CH that the filtration associated to the separation process in hydrocyclones resulted in changes in the performance of those separators.