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High-speed aircraft flow transition characteristic obtaining method and system

A high-speed aircraft and transition technology, applied in the direction of instruments, special data processing applications, electrical digital data processing, etc., can solve problems such as the inability to apply high-speed flow transition process simulation

Active Publication Date: 2018-06-22
TSINGHUA UNIV +1
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Problems solved by technology

[0008] However, current hybrid methods are limited to fully turbulent calculations and cannot be applied to the simulation of high-speed flow transition processes

Method used

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  • High-speed aircraft flow transition characteristic obtaining method and system
  • High-speed aircraft flow transition characteristic obtaining method and system

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Embodiment Construction

[0038] The specific implementation manners of the present invention will be further described in detail below in conjunction with the accompanying drawings and embodiments. The following examples are used to illustrate the present invention, but are not intended to limit the scope of the present invention.

[0039] figure 1 A method for obtaining flow transition characteristics of a high-speed aircraft according to an embodiment of the present invention, comprising:

[0040] S1. Establish a full-scale model of the high-speed aircraft, and obtain an optimal grid corresponding to the full-scale model according to the shape parameters of the full-scale model;

[0041] Specifically, the accuracy of numerical calculation results and the efficiency of the calculation process are greatly affected by the grid quality. Successful and efficient calculation results can only be obtained when the mesh generation and the algorithm for solving the flow field are well matched.

[0042] S2....

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Abstract

The invention provides a high-speed aircraft flow transition characteristic obtaining method and system. The method comprises the steps that a full size model of a high-speed aircraft is built, and anoptimal grid corresponding to the full size model is obtained according to shape parameters of the full size model; incoming flow parameters of a high-speed aircraft and boundary condition parametersof the high-speed aircraft are obtained; according to the optimal grid, the incoming flow parameters and the boundary condition parameters, a surface boundary layer flow transition of the high-speedaircraft is simulated through a character-king transition mode based on Reynolds average, a separate flow transition of the high-speed aircraft is simulated through a Reynolds average-large eddy simulation hybrid method, and the transition initiation point of the high-speed aircraft and the transition area length of the high-speed aircraft are obtained. Accordingly, the method and system can be successfully applied to simulation of the flow transition of the aircraft from the subsonic speed to the hypersonic speed, the numerical precision is high, and the result is reliable.

Description

technical field [0001] The present invention relates to the technical field of high-speed aircraft, and more specifically, to a method and system for acquiring flow transition characteristics of a high-speed aircraft. Background technique [0002] The transition process from laminar flow to turbulent flow has an important influence on the design of high-speed aircraft. Since the wall friction and heat transfer coefficient in the transition region will increase sharply, even higher than the value in the fully turbulent region, delaying the transition of the boundary layer flow on the surface of a high-speed aircraft can greatly reduce fuel consumption and make the selection of thermal protection materials more efficient. flexible. [0003] However, in the design of high-speed aircraft engines, the transition must be promoted. If the flow at the inlet of the engine inlet is in a laminar flow state, separation bubbles will easily be generated and gas capture will be affected. ...

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/20Y02T90/00
Inventor 符松王亮罗金玲汤继斌
Owner TSINGHUA UNIV
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