Simulating the Aerodynamics Profiles of NACA 4312 Airfoil in Various Incoming Airspeed and Gurney Flap Angle

Sumaryada, Tony; Jaya, Achmad Muharam; Kartono, Agus Priyono

doi:10.31758/omegajphysphyseduc.v4i1.1

Cited by 2 publications

(1 citation statement)

References 6 publications

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“…The research results indicated that, with an increase in height, both lift and drag increased, and a Gurney flap height of 1.5% chord length performed the best within the studied range. Sumaryada et al [11] examined the effects of different Gurney flap installation angles on the aerodynamic performance of the NACA4312 foil. After simulating the aerodynamic performance of the foil at different wind speeds, they found that, within the range of the installation angle studied, increasing the installation angle led to an increase in lift and a decrease in drag of the foil.…”

Section: Introductionmentioning

confidence: 99%

Multi-Objective Optimization Design of Dynamic Performance of Hydrofoil with Gurney Flap

Zhang,

Yao,

Ding

et al. 2024

JMSE

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The horizontal axis tidal turbine, as a crucial device for capturing tidal energy, has gained significant attention because it has better energy efficiency performance. Enhancing the performance of foils, a vital part of tidal turbine blades, can significantly improve tidal turbine performance. Among numerous methods to enhance the foil performance, the Gurney flap has gained significant attention due to its avoidance of complex structural design. Currently, there is limited research on optimizing the design of Gurney flaps while considering the dynamic performance of foils. In this study, the S809 foil with a blade cross-section was selected as the research subject, a multi-objective optimization design platform was created by integrating a multi-objective optimization algorithm with Computational Fluid Dy-namics (CFD) numerical simulation techniques. The objective of this platform is to enhance the dynamic performance of the hydrofoil by optimizing the geometric structure of the Gurney flap. The improvement of dynamic lift and the size of the dynamic stall hysteresis loop are used as objective variables in this study to evaluate the hydrofoil’s dynamic performance. The optimal Latin hypercube design method is used in the optimization process to choose sample locations, and the Kriging approximation model is used to determine the relationship between the design variables and the objective variables. Meanwhile, the Non-Dominated Sorting Genetic Algorithm-II (NSGA-II) is used to create a multi-objective optimization platform for solving the optimization problem, and the optimized results are validated using CFD. Comparative validation results show that quantifying the dynamic performance during hydrofoil pitching oscillation and using the optimal Latin hypercube design method and Kriging approximation model for optimizing the Gurney flap structure is rational and accurate. This study explores the mechanism of the Gurney flap through in-depth CFD numerical simulations and finds that the Gurney flap affects the flow characteristics at the hydrofoil’s trailing edge, thereby influencing the performance. It increases the pressure difference between the pressure and suction surfaces, thus enhancing the hydrofoil’s lift. Finally, this article provides three recommended parameters to improve the dynamic performance of the hydrofoil. This research can serve as a reference for the application of Gurney flaps in tidal turbine blade design.

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Section: Introductionmentioning

confidence: 99%

Multi-Objective Optimization Design of Dynamic Performance of Hydrofoil with Gurney Flap

Zhang,

Yao,

Ding

et al. 2024

JMSE

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Numerical Analysis of the Aerodynamic Characteristics of NACA-4312 Airfoil

Pranto

Inam

2020

JEA

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The aim of the work is to investigate the aerodynamic characteristics such as lift coefficient, drag coefficient, pressure distribution over a surface of an airfoil of NACA-4312. A commercial software ANSYS Fluent was used for these numerical simulations to calculate the aerodynamic characteristics of 2-D NACA-4312 airfoil at different angles of attack (α) at fixed Reynolds number (Re), equal to 5×10^5 . These simulations were solved using two different turbulence models, one was the Standard k-ε model with enhanced wall treatment and other was the SST k-ω model. Numerical results demonstrate that both models can produce similar results with little deviations. It was observed that both lift and drag coefficient increase at higher angles of attack, however lift coefficient starts to reduce at α =13° which is known as stalling condition. Numerical results also show that flow separations start at rare edge when the angle of attack is higher than 13° due to the reduction of lift coefficient.

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Simulating the Aerodynamics Profiles of NACA 4312 Airfoil in Various Incoming Airspeed and Gurney Flap Angle

Abstract: Simulations of the aerodynamics performance of NACA 4312 airfoil at various gurney flap angles and incoming airspeed (wind velocities) have been conducted. The gurney flap's size was set at 5.0% length of the chord line.

Cited by 2 publications

References 6 publications

Multi-Objective Optimization Design of Dynamic Performance of Hydrofoil with Gurney Flap

Multi-Objective Optimization Design of Dynamic Performance of Hydrofoil with Gurney Flap

Numerical Analysis of the Aerodynamic Characteristics of NACA-4312 Airfoil

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