Numerical Simulation Study of a Two-dimensional Wing Encountering Air Turbulence
The ultimate goal of the wake interval reduction method is to calculate the wake interval between the two aircraft in real time based on the wind field over the airport and the pairing of the front and rear aircraft.Due to the complex environment of the background wind field during the approach phase,in order to achieve the goal of this phase,it is necessary to study the wake field of the front aircraft for different background wind fields.In this paper,turbulence,a common wind structure near the ground,is se-lected for CFD numerical simulation,and the flow field structure of NACA4415 two-dimensional airfoil when encountering turbu-lence is observed and explained.The simulation results show that when the plane is tossed by the air current,the two-dimensional wing of the two-dimensional wing will be accelerated by the rupture of the wake vortex field due to the vertical fluctuation of the flow field.Turbulence that fluctuates up and down with the cycle will be generated behind the wing,and the turbulence intensity will de-crease when the turbulence intensity crosses the streamline during the backward development process.After passing the wing,the direction of the streamline near the trailing edge of the wing is mainly affected by the angle between the leading edge of the wing and the incoming flow.After about twice the chord length,it will rise or fall under the influence of the background wind field,and the period is consistent with the incoming flow period.
CFDnumerical simulationwingtip vortexturbulencereduce wake interval
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