扇翼飞行器翼型附面层控制数值模拟

doi:10.7527/S1000-6893.2016.0111

Abstract

Abstract:

Based on the specific geometry of fanwing aircraft airfoil and flow field characteristics, we modify the airfoil by installation of control valves at the trailing edge and below the arc-groove. In order to take advantage of the lower pressure vortex to control the boundary layer of the trailing edge by adjusting the size of valve. CFD method is used to analyze the control method's mechanism and the influence of relative parameter. The calculation results show that when the size of the valve opens to 10 mm, the modified airfoil's maximum lift coefficient and stall angle of attack and the lift and thrust coefficients with the same angle of attack are greater than the basic airfoil. With the increase of the size of valve, the modified airfoil's maximum lift coefficient and stall angle of attack are reduced, but before stalling, the modified airfoil's lift coefficient is larger than the basic airfoil at the same angle of attack. This method gives us a new way to improve fanwing's aerodynamic performance, decrease power consumption and extend the flight range, which lays a certain theoretical foundation for the practical use of the fanwing aircraft as soon as possible.

Key words: fanwing, flow control, lift enhancement drag reduction, flight range, eccentric vortex

CLC Number:

V211.3

DU Siliang, LU Zhiming, TANG Zhengfei. Numerical simulation on boundary layer control method of fanwing aircraft airfoil[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2016, 37(6): 1781-1789.

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Numerical simulation on boundary layer control method of fanwing aircraft airfoil

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