Sonic-boom prediction method of supersonic aircraft

A prediction method and technology for aircraft, applied in the fields of instruments, special data processing applications, electrical digital data processing, etc., can solve the problems of sonic boom wind tunnel test technology that has not been carried out before, typical flow field parameters and shock wave large calculation error, accuracy and difference. Resolution loss, etc.

Active Publication Date: 2018-06-15
AVIC SHENYANG AERODYNAMICS RES INST
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Problems solved by technology

In the long-distance calculation, due to the loss of accuracy and resolution, it will cause large calculation errors in typical flow field parameters and shock waves
[0006] Judging from the current data, the research on the characteristics of sonic boom has become the key technology for the development o

Method used

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  • Sonic-boom prediction method of supersonic aircraft
  • Sonic-boom prediction method of supersonic aircraft
  • Sonic-boom prediction method of supersonic aircraft

Examples

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[0107] Example 1

[0108] A kind of supersonic aircraft sonic boom prediction method proposed by the present invention is further described below with a specific application example:

[0109] In the specific embodiment, the supersonic aircraft adopted is the F-5E aircraft, and its relevant parameters are shown in Table 1:

[0110] Table 1

[0111] parameter

[0112] Applying the method in the present invention to predict the sonic boom characteristics of a supersonic aircraft mainly consists of the following steps:

[0113] 1. According to the configuration of the supersonic aircraft and the inflow conditions shown in Table 1, the CFD solution of the supersonic aircraft is carried out, and the main solution equation is the Euler equation.

[0114] 2. Given the near-field static pressure characteristics of the aircraft. From the supersonic space flow field obtained in step 1, the pressure distribution at 2 times the characteristic length below the aircraft is extra...

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Abstract

The invention relates to a sonic-boom prediction method of a supersonic aircraft. The method uses a method of combination of CFD numerical-simulation and far-field extrapolation to realize sonic-boomprediction of the supersonic aircraft, and includes the steps of: drawing structural or non-structural grids satisfying requirements, and determining a CFD solver and a solving method; carrying out CFD solving of the supersonic aircraft; extracting near-field static-pressure features of the aircraft; approximately representing the shape of an initial waveform through any number of linear line segments; periodically solving first-order coupled-differential-equations, which describe waveform parameter changes, to obtain information of a waveform of a next moment; and repeating execution until anoverpressure value at a specified height is obtained. According to the method, influences of factors of an aircraft shape, shock waves, expansion waves and the like are systematically simulated, calculation precision is much higher than that of traditional linear methods, and propagation situations of pressure waves in an atmosphere are more realistically simulated at the same time.

Description

technical field [0001] The invention relates to the field of computational fluid dynamics, in particular to a method for predicting a sonic boom of a supersonic aircraft. Background technique [0002] With the progress and continuous accumulation of various disciplines and technologies such as aerodynamics, electronic systems, materials and manufacturing processes, the conditions and timing for the development of supersonic aircraft have gradually matured. It can be foreseen that in the future civil aviation market, supersonic large passenger aircraft will gradually become the protagonist. This is one of the inevitable directions for human aviation to move towards faster, more economical and environmentally friendly, safer and more comfortable. [0003] A sonic boom is a nonlinear aeroacoustic phenomenon. When an aircraft flies at supersonic speed, its nose, wings, and tail will generate shock waves; on the other hand, due to the change of the shape of the fuselage, there w...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/20G06F2119/10Y02T90/00
Inventor 冷岩钱占森
Owner AVIC SHENYANG AERODYNAMICS RES INST
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