Purpose

This study aims to evaluate the amount of entropy generation around the NACA 0012 airfoil. This study takes place in four angles of attack of 0°, 5°, 10° and 16° and turbulent regime. Also, the variation in the amount of generated entropy by the changes in temperature and Mach number is investigated.

Design/methodology/approach

The governing equations are solved using computational fluid dynamics techniques. The continuity, momentum and energy equations and the equations of the SST k-ω turbulence model are solved. The entropy generation at different angles of attack is calculated and compared. The effect of various parameters in the generation of entropy is presented.

Findings

Results show that the major part of the entropy generation is at the tip of the airfoil. Also, increasing the angle of attack will increase the entropy generation. Also, results show that with increasing the temperature of air colliding with the airfoil, the production of entropy decreases.

Originality/value

Entropy generation is investigated in the NACA 0012 airfoil at various angles of attack and turbulent flow using the SST turbulence model. Also, the effects of temperature and Mach number on the entropy generation are investigated.

中文翻译：

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研究湍流中翼型周围的熵产生

目的

本研究旨在评估NACA 0012机翼周围的熵产生量。这项研究以0°，5°，10°和16°的四个迎角和湍流状态进行。另外，研究了随着温度和马赫数的变化而产生的熵的量的变化。

设计/方法/方法

使用计算流体动力学技术求解控制方程。求解了连续性，动量和能量方程以及SSTk-ω湍流模型的方程。计算并比较了不同迎角下的熵生成。提出了各种参数在熵产生中的作用。

发现

结果表明，熵产生的主要部分位于机翼的尖端。同样，增加迎角将增加熵的产生。而且，结果表明，随着空气温度与翼型相撞，熵的产生降低。

创意/价值

使用SST湍流模型研究了NACA 0012翼型在不同迎角和湍流下的熵产生。此外，研究了温度和马赫数对熵产生的影响。