Low span chord ratio aerofoil type designing method considering three-dimensional effect

A small aspect ratio, airfoil design technology, applied in the direction of computing, special data processing applications, instruments, etc., can solve problems such as the inability to guarantee the correctness of design results, and achieve the effect of improving transonic and supersonic performance

Inactive Publication Date: 2016-10-12
NORTHWESTERN POLYTECHNICAL UNIV
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Problems solved by technology

Therefore, the traditional two-dimensional airfoil design cannot guarantee the corre

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  • Low span chord ratio aerofoil type designing method considering three-dimensional effect
  • Low span chord ratio aerofoil type designing method considering three-dimensional effect
  • Low span chord ratio aerofoil type designing method considering three-dimensional effect

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[0054] The embodiments of the present invention are described in detail below, and the embodiments are exemplary and intended to explain the present invention, but should not be construed as a limitation of the present invention.

[0055] Modern advanced fighters generally require superior performance in the range from subsonic to supersonic, so the wings generally adopt thin wings with small aspect ratio and large sweep angle. In the aerodynamic design of this type of wing, it is characterized by the dominance of three-dimensional flow. It is generally believed that the plane shape of the wing plays a decisive role, but the airfoil is still very important for the design of a small aspect ratio wing: the airfoil Transonic lift-drag characteristics directly affect the range of the aircraft, supersonic drag characteristics directly affect the supersonic cruise capability of the aircraft, and the camber of the airfoil directly affects the maneuverability of the aircraft. If the i...

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Abstract

The invention provides a low span chord ratio aerofoil type designing method considering a three-dimensional effect. The method sequentially comprises the steps of building parameterized initial foil type data; determining a foil type design status and a designed target; adopting a Latin hypercube sampling method, a plurality of sample foil type data is obtained; building an agent model; building an optimization population and adopting a multi-target optimization algorithm for optimizing the optimization population. With the combination of a classic foil-type parameterizing method, the agent model technology and the multi-target optimization algorithm, the efficient and reliable fighter low-span-chord ratio aerofoil type designing method, the low span chord ratio aerofoil type performance is ensured through foil type geometric and aerodynamic pneumatic performance under the two-dimensional environment, the transonic speed and the supersonic speed performance of a aerofoil can be greatly improved through the foil type designed by the model, and the voyage and operation radius are increased while the aero supersonic speed cruising capacity is improved.

Description

technical field [0001] The invention relates to the technical field of wing airfoil design and the technical field of computer simulation and numerical optimization, in particular to a small aspect ratio wing airfoil design method considering three-dimensional effects. Background technique [0002] For a wing with a large aspect ratio, the aerodynamic characteristics of most of the wing surface are close to two-dimensional flow, and the three-dimensional flow is only in the root and tip of the wing. Therefore, the aerodynamic characteristics of the airfoil will determine the aerodynamic characteristics of the entire wing. The choice of airfoil is very important for the design of high aspect ratio wings. For modern advanced fighter jets and high-maneuvering UAVs, it is generally required to have superior performance in the range from subsonic to supersonic, so the wings generally adopt thin wings with small aspect ratio and large sweep angle. For small aspect ratio or large ...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15Y02T90/00
Inventor 高正红王超夏露赵欢
Owner NORTHWESTERN POLYTECHNICAL UNIV
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