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New methodology combining neural network and extended great deluge algorithms for the ATR-42 wing aerodynamics analysis

机译:结合神经网络和扩展大洪水算法的新方法用于ATR-42机翼空气动力学分析

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摘要

The fast determination of aerodynamic parameters such as pressure distributions, lift, drag and moment coefficients from the known airflow conditions (angles of attack, Mach and Reynolds numbers) in real time is still not easily achievable by numerical analysis methods in aerodynamics and aeroelasticity. A flight parameters control system is proposed to solve this problem. This control system is based on new optimisation methodologies using Neural Networks (NNs) and Extended Great Deluge (EGD) algorithms. Validation of these new methodologies is realised by experimental tests using a wing model installed in a wind tunnel and three different transducer systems (a FlowKinetics transducer, an AEROLAB PTA transducer and multitube manometer tubes) to determine the pressure distribution. For lift, drag and moment coefficients, the results of our approach are compared to the XFoil aerodynamics software and the experimental results for different angles of attack and Mach numbers. The main purpose of this new proposed control system is to improve, in this paper, wing aerodynamic performance, and in future to apply it to improve aircraft aerodynamic performance.
机译:仍然无法通过空气动力学和空气弹性的数值分析方法来快速,实时地从已知的气流条件(迎角,马赫数和雷诺数)快速确定空气动力学参数,例如压力分布,升力,阻力和力矩系数。为了解决这个问题,提出了一种飞行参数控制系统。该控制系统基于使用神经网络(NN)和扩展大洪水(EGD)算法的新优化方法。这些新方法的验证是通过使用安装在风洞中的机翼模型和三个不同的传感器系统(FlowKinetics传感器,AEROLAB PTA传感器和多管压力计管)进行试验测试来确定压力分布的。对于升力,阻力和力矩系数,将我们的方法的结果与XFoil空气动力学软件进行了比较,并比较了不同迎角和马赫数的实验结果。这种新提出的控制系统的主要目的是在本文中改善机翼的空气动力性能,并在将来将其应用于改善飞机的空气动力性能。

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