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Dynamic numerical simulation method for external flow field of multi-element airfoil of airplane

A numerical simulation and multi-segment wing technology, applied in electrical digital data processing, special data processing applications, instruments, etc., to achieve accurate and reliable simulation results

Inactive Publication Date: 2017-04-26
SHANGHAI UNIV OF ENG SCI
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Problems solved by technology

[0005] However, for the problem of airfoil displacement motion in the process of aircraft falling, the steady method cannot be used to simulate

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  • Dynamic numerical simulation method for external flow field of multi-element airfoil of airplane

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Embodiment

[0029] Such as figure 1 As shown, an aircraft multi-segment airfoil external flow field dynamic numerical simulation method, the method includes the following steps:

[0030] (1) Establish a multi-segment airfoil model with leading edge slats and trailing edge flaps and import fluent software;

[0031] (2) Construct the vertical falling motion function of the aircraft model and import it into Fluent software;

[0032] (3) Select the turbulence model;

[0033] (4) Set simulation parameters, including fluid parameters, airfoil material parameters, working environment parameters, boundary condition parameters, dynamic mesh update model, solution method and solution accuracy;

[0034] (5) Boundary initialization, setting the monitoring window, setting iteration parameters, setting automatic screenshots, running fluent software, and performing automatic calculations, so as to obtain the change graph of the fluid flow parameters around the airfoil during the vertical drop of the aircraft, in...

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Abstract

The invention relates to a dynamic numerical simulation method for an external flow field of a multi-element airfoil of an airplane. The method comprises the steps that 1, an airplane model with a leading edge slat, a trailing edge flap and the multi-element airfoil is established and imported into fluent software; 2, a vertical descending motion function of the airplane model is constructed and imported into the fluent software; 3, a turbulence model is selected; 4, simulation parameters are set, including fluid parameters, airfoil material parameters, work environment parameters, boundary condition parameters, a dynamic mesh updating model, a solution method and solution precision; 5, the fluent software is run, and a flow parameter variation diagram, including a speed, pressure and temperature variation diagram, of fluid around the airfoil in the vertical descending process of the airplane is acquired. Compared with the prior art, dynamic numerical values of the external flow field in the landing process of the airplane can be effectively acquired, and reference can be conveniently provided for assessment of rising and landing performance of the airplane and design of a high lift device.

Description

Technical field [0001] The invention relates to a numerical simulation method for the external flow field of an aircraft, in particular to a dynamic numerical simulation method for the external flow field of an aircraft multi-section airfoil. Background technique [0002] During take-off and landing of an aircraft, because it is close to the ground, it is likely to be affected by ground effects. The so-called ground effect is a hydrodynamic effect that reduces the induced drag of the aircraft while achieving a higher lift-to-drag ratio than flying in the air: when the moving aircraft falls very close to the ground (or water), the entire aircraft body As the pressure difference increases, the lift will increase suddenly. Aircraft usually use lift-increasing devices to increase the lift of the aircraft at low speeds, increase load, increase range, reduce aircraft weight, etc. The lift-increasing devices are mostly composed of leading edge slats, main wings and trailing edge flaps....

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/20Y02T90/00
Inventor 张鑫鹏匡江红吕鸿雁
Owner SHANGHAI UNIV OF ENG SCI
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