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Method for evaluating aerodynamic performance of high-speed aircraft

A high-speed aircraft and aircraft technology, applied in the field of aircraft research, can solve problems such as lack of prediction formulas and strong Reynolds comparisons, inaccurate aerodynamic performance evaluation results, and unclear physical meaning of prediction methods, so as to achieve accurate evaluation and reduce prediction errors , to achieve the effect of aerodynamic performance

Active Publication Date: 2022-04-12
CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT
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  • Abstract
  • Description
  • Claims
  • Application Information

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Problems solved by technology

In 2014, Helm et al. proposed a prediction model for near-wall velocity and temperature fluctuations, which can give better velocity and temperature fluctuations. The prediction model for temperature fluctuations in the near-wall region is similar to the model for velocity fluctuations. However, the prediction formula and The lack of obvious correlation between the strong Reynolds analogy makes the physical meaning of the prediction method unclear and the error is large
[0005] At present, there is no prediction method for wall friction and heat flow fluctuations of compressible wall turbulent flow with accurate prediction, good universality and clear physical meaning. Inaccurate

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  • Method for evaluating aerodynamic performance of high-speed aircraft
  • Method for evaluating aerodynamic performance of high-speed aircraft
  • Method for evaluating aerodynamic performance of high-speed aircraft

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Embodiment 1

[0053] Please refer to figure 1 , figure 1 It is a schematic flow chart of a method for evaluating the aerodynamic performance of a high-speed aircraft. Embodiment 1 of the present invention provides a method for evaluating the aerodynamic performance of a high-speed aircraft. The method includes:

[0054] Construct the prediction model of aircraft wall frictional resistance fluctuation and the prediction model of aircraft wall heat flow fluctuation;

[0055] The first intermediate quantity data and the second intermediate quantity data are obtained through numerical simulation or experimental calibration, and the first intermediate quantity data includes: aircraft wall friction pulsation prediction related modulation coefficient, aircraft wall friction pulsation prediction related universal signal, aircraft Wall surface friction pulsation prediction related phase difference and aircraft wall friction pulsation prediction related linear random prediction kernel function; the ...

Embodiment 2

[0122] Embodiment 2 of the present invention introduces this method in detail in conjunction with specific examples:

[0123] In the application, the modulation coefficient in the model, the phase difference of the modulation pair superposition, and the linear correlation kernel function need to be directly calibrated by numerical simulation at a medium Reynolds number / high Reynolds number, and can be applied to other parameters after calibration.

[0124] Input signal during application: large-scale velocity pulsation in the outer zone, which can be given by low-resolution numerical simulation or experimental measurement; output signal: wall friction and heat flow pulsation signals.

[0125] The accuracy of the prediction results of this method is verified by the joint probability density (PDF). The calculation parameters are: incoming flow Mach number 3.0, incoming flow total temperature 300K, wall temperature 420K, and Reynolds number 42000. Such as Figure 2-Figure 5 show...

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Abstract

The invention discloses a method for evaluating aerodynamic performance of a high-speed aircraft, which relates to the field of aircraft research, and is based on the superimposed effect and modulation effect of an outer-area large-scale turbulence structure on near-wall turbulence pulsation according to generalized Reynolds comparison of speed-temperature pulsation. And establishing a high Reynolds number wall turbulence wall surface friction resistance and heat flow pulsation prediction model, thereby realizing accurate prediction of compressible high Reynolds number turbulence wall surface friction resistance and heat flow pulsation based on the flow field measurable signal, and further realizing accurate evaluation of the aerodynamic performance of the high-speed aircraft.

Description

technical field [0001] The invention relates to the field of aircraft research, in particular to a method for evaluating the aerodynamic performance of a high-speed aircraft. Background technique [0002] Aircraft aerodynamic design and evaluation is an important link in the process of aircraft development. Aircraft aerodynamic design is the process of optimizing the layout and geometric parameters of the aircraft to improve aerodynamic and flight performance. Aircraft performance evaluation refers to the evaluation of the aerodynamic, flight, flight control, stealth, structural strength, power and other performance of the aircraft through wind tunnel tests, numerical calculations, flight simulation, flight tests and other means during the design and use of the aircraft. the process of. The two are an organic whole. The pros and cons of aircraft aerodynamic design need to be judged through evaluation, and the innovation of aerodynamic design will continue to promote the de...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G06F30/20G06F30/28G06F111/08G06F111/10G06F113/08G06F119/14
Inventor 余明傅亚陆刘朋欣袁先旭
Owner CALCULATION AERODYNAMICS INST CHINA AERODYNAMICS RES & DEV CENT