NACA 4415 翼面上各类气流的数值分析

Md. Lutfar, Rahman Sarkar, M. Z. I. Bangalee
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摘要

因为有了高速飞行的飞机,与地球另一端的距离似乎更近了,仿佛就在隔壁。由于对机翼的研究,航空航天工程经历了一场革命。这项研究工作的重点是分析 NACA 4415 机翼在湍流中的气动性能,同时考虑马赫数和雷诺数。本研究考虑的弦长为 和 。计算流体动力学用于确定升力、阻力和俯仰力矩及其各自的非尺寸系数。结果发现,最大升力和力矩在攻角之后产生,停滞区在机翼后方急剧增大,与攻角的增量成正比。此外,通过分析压力和速度等值线,研究了压力和速度对机翼表面各点的影响:85-91, 2024 (January)
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Numerical Analysis of Various Types of Flows Over NACA 4415 Airfoil
Because of the high-speed aircrafts, the distance to the other side of the world seems to be closer, as if it were situated just next door. Aerospace engineering has undergone a revolution thanks to research into airfoils. This research work has been focused on analyzing the aerodynamic performances of the NACA 4415 airfoil in turbulent flows while Mach numbers,  and Reynolds numbers,  have been taken into account. The chord length of  and  have been considered for this study. Computational fluid dynamics were employed to determine the lift, drag, and pitching moment forces, as well as their respective non-dimensional coefficients. As a result, maximum lift, moment forces have been found after the  angle of attacks, and stagnation areas are increasing dramatically behind the airfoil, proportion to the increments with the angle of attack. Additionally, the effects of pressure and velocity on every point of the airfoil's surface were studied through the analysis of pressure and velocity contours. Dhaka Univ. J. Sci. 72(1): 85-91, 2024 (January)
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