低雷诺数下俯仰NACA 0012翼型的非定常空气动力学

IF 1.5 4区工程技术 Q2 ENGINEERING, AEROSPACE

International Journal of Micro Air Vehicles Pub Date : 2019-01-01 DOI:10.1177/1756829319890609

D. Kurtulus

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引用次数: 6

摘要

本文旨在对NACA 0012翼型在Re下的小振幅振荡进行数值研究 = 1000.机翼围绕四分之一弦点正弦俯仰，俯仰幅度为1°，大约为平均迎角。计算的平均攻角范围为0°至60°，俯仰频率为1 Hz和4 赫兹。与非振荡条件相比，研究了平均攻角和俯仰频率对瞬时力以及涡流结构的影响。结果表明，在所研究的条件下，翼型的振荡会改变气动载荷的振荡幅度。俯仰翼型在1时的瞬时阻力系数始终为正赫兹。同时，在一些时间间隔内，俯仰运动的瞬时阻力系数在4时变为负值 Hz，平均攻角为3°至36°。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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Unsteady aerodynamics of a pitching NACA 0012 airfoil at low Reynolds number

The present paper aims to investigate numerically small amplitude oscillation of NACA 0012 airfoil at Re = 1000. The airfoil is sinusoidally pitching around the quarter chord point with 1° pitch amplitude about a mean angle of attack. The computations are performed for mean angles of attack ranging from 0° to 60° and for pitching frequencies of 1 Hz and 4 Hz. The effect of the mean angle of attack and pitching frequency on the instantaneous forces as well as the vortex structure is investigated in comparison with the non-oscillatory conditions. It was shown that airfoil oscillations at the investigated conditions change the amplitude of oscillation of the aerodynamic loads. The instantaneous drag coefficient is always positive for pitching airfoil at 1 Hz. In the meantime, there are time intervals where instantaneous drag coefficient becomes negative for pitching motion at 4 Hz for mean angles of attack from 3° to 36°.

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来源期刊

International Journal of Micro Air Vehicles ENGINEERING, AEROSPACE-

CiteScore

3.00

自引率

7.10%

发文量

审稿时长

>12 weeks

期刊介绍： The role of the International Journal of Micro Air Vehicles is to provide the scientific and engineering community with a peer-reviewed open access journal dedicated to publishing high-quality technical articles summarizing both fundamental and applied research in the area of micro air vehicles.