Effect of Reynolds Number on the Aerodynamic Performance of NACA0012 Aerofoil

Jha, Shailesh Kumar; Gautam, Uddipta; Narayanan, S.; Dhas, LA Kumaraswami

doi:10.1088/1757-899x/377/1/012129

Cited by 4 publications

(3 citation statements)

References 2 publications

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“…At the same time, in order to obtain more reliable simulation results, the grids near the wing are encrypted. Te comparison between the lift coefcient obtained in the manuscript and the results of Jha et al [29] is displayed in Figure 3.…”

Section: Model Validationmentioning

confidence: 69%

Flow Characteristics of a Fish-Like Body Based on Taguchi Method under Different Strouhal Numbers

Guo

Zheng

et al. 2022

Mathematical Problems in Engineering

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In the investigations of fish swimming, the relationship between fish swimming and the corresponding characteristics of flow field attracts lots of attention. In this paper, the influence of different Strouhal numbers on the flow field characteristics and mechanical characteristics of fish-like body is investigated. It is found that the strength of the anti-Karman vortex and the thrust on the fish-like body are affected by the Strouhal number. When the Strouhal number is small, the thrust coefficient is small but the propulsion efficiency is high. Similarly, when the Strouhal number is large, the thrust coefficient is large and the propelling efficiency is low. In order to better reveal the swimming status of the flexible body of the fish imitation, the effect of the Strouhal number is analyzed in detail in this paper. Besides, the influence of the three parameters in the Strouhal number formula on the flow field characteristics and thrust coefficient of the fish-like body is further investigated by the Taguchi method. The thrust coefficient is positively correlated with the swing amplitude and frequency, which is found to be negatively correlated with the inflow velocity. Swing amplitude and swing frequency are the main factors affecting the thrust coefficient; there is little effect of the inflow velocity on the thrust coefficient.

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Section: Model Validationmentioning

confidence: 69%

Flow Characteristics of a Fish-Like Body Based on Taguchi Method under Different Strouhal Numbers

Guo

Zheng

et al. 2022

Mathematical Problems in Engineering

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“…Using the NACA 0012 symmetric airfoil (non-camber) consists of four numbers in the NACA series and indicates that the airfoil does not have any camber, and the number (12) indicates that the thickness of the airfoil is 12 % of the chord length of the airfoil.…”

Section: Numerical Studymentioning

confidence: 99%

“…A numerical simulation of turbulent flow was carried out by Sahoo and Maity [11] for wings (NACA 0012 and NACA 4412, S809), and the NACA 4412 airfoil resulted in a higher lift coefficient than both NACA 0012 and S809 due to its thin outer profile and camber height. In 2018 [12], the dynamic properties of the NACA 0012 airfoil with different Reynolds numbers were demonstrated experimentally and numerically by Jha et al Yousefi and Razeghi [13] studied the effect that Reynolds number and angle of attack have on the location of the turbulent-laminar transition based on Reynolds number and angle of attack. As the angle of attack increases.…”

Section: Introductionmentioning

confidence: 99%

Numerical Simulation of the Aerodynamic Characteristics of NACA0012 Airfoil Based on Operational Parameters

Mula,

Abdulwahid

2023

BJES

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This study investigated the performance of symmetric airfoils of type NACA0012 numerically under different operating conditions. It has been assumed that the study involves steady state, non-compressive, and turbulent flows. The operating fluid was air. The effect of Reynolds number and angle of attack on lift and drag coefficients, pressure distribution, and velocity distribution was investigated. ANSYS FLUENT has been used to solve the numerical model by using continuity equations, Navier-Stokes equations, and the appropriate K-ω SST perturbation model. This study shows a clear difference between the pressure coefficient of the lower and upper surfaces of the airfoil at high Reynolds numbers, indicating higher lift at high Reynolds numbers. As the maximum stall angle of the airfoil NACA0012 is 14° after which it decreases significantly, a direct relationship was observed between lift and drag coefficients and angle of attack.

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