Numerical Simulation of the Aerodynamic Characteristics of NACA0012 Airfoil Based on Operational Parameters (original) (raw)
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Open Engineering, 2024
Using computational models and low-speed wind tunnel tests, the aerodynamic characteristics of the NACA 0012 airfoil with low Re numbers of (8 × 10 4 , 2 × 10 5 , 3 × 10 5 , and 4 × 10 5) and angle of attack (AOA) ranging from 0°t o 18°by two steps are examined. Using the same 3-D wind tunnel dimensions, numerical simulations were run. The software program ANSYS FLUENT was used to solve the mathematical model using the continuity equation, the Navier-Stokes equations, and the k-ω shearstress transport turbulence model. Findings demonstrate that at all AOAs, there is a direct relationship between Reynolds numbers (Re), lift and drag coefficients, kinetic energy, and stall angle. The lift coefficient rises linearly as the AOA increases, peaking at 14°, the stall angle at higher Reynolds number. The lift coefficient was found to decline when the AOA was increased further, reaching its minimal value at an AOA of 18°. With a greater AOA, the airfoil's drag coefficient rises, creating turbulent flow. The eddies produced by the turbulence cause the flow to start separating from the airfoil surface as turbulence increases. As a result, the airfoil lift coefficient drops, and its drag coefficient rises at the same time, leading to poor performance. The validation of the numerical results through wind tunnel experiments provided confidence in the findings of the study.
A Computational Case Study on Aerodynamic parameters of NACA symmetrical Aerofoils
2021
The objective of this research is to determine the velocity and pressure field of NACA-0022 airfoil by solving the governing equation using Ansys fluent and to validate the result data of 10degree angle of attack of an airfoil with the experimental data provided by NASA such as1)Pressure coefficient. 2)Lift and drag coefficient.Also to determine the stalling angle by changing the angle of attack to 4,6,10,15,19 degree. During the research we found that The NACA 4 digit airfoil have a higher efficiency at Tip speed ratios of 7. The study of flow over NACA 4 digit airfoil is done for the Reynolds number (Re) of 105 and Richardson number (Ri) ranging from -0.5 to +0.7 at zero degree angle of attack. It has been found that with the increase in Ri, the Cl decreases almost linearly. On the contrary with the increase in Ri, the Cd increases. We found that the surface heating results in the early flow separation and is attributed to such behavior for Cl and Cd. Early flow separation leads t...
Journal of Academic Research, 2024
Article information This article seeks to numerically analyze the aerodynamic performance of the NACA-0015 airfoil blade, with a focus on examining the effects of varying the angle of attack on lift, drag, and stall characteristics. The design of an airplane's wing is critical for maximizing lift while minimizing drag, both of which are regulated by adjusting the angle of attack during flight. To explore these dynamics, Computational Fluid Dynamics (CFD) analysis is employed using ANSYS software, particularly its FLUENT tool, to simulate fluid flow around the airfoil. The airfoil geometry, with a chord length of 0.06 meters and a span of 0.25 meters, is modeled in ANSYS Design Modeler. The CFD simulations are performed using the Realizable k-epsilon turbulence model, analyzing angles of attack ranging from 0° to 18° under low Reynolds numbers (6×10 4 to1.6×10 5). Through this comprehensive approach, the study provides a wider understanding of the flow characteristics over the NACA-0015 airfoil, contributing to the precise knowledge of airfoil performance in aviation applications.
Numerical and Experimental Investigation of Aerodynamics Characteristics of NACA 0015 Aerofoil
International journal of engineering technologies, 2017
An aerofoil is a streamline body. Symmetric aerofoil (NACA 0015) is used in many applications such as in aircraft submarine fins, rotary and some fixed wings. The ultimate objective of an aerofoil is to obtain the lift necessary to keep an airplane in the air. But construction of the blade with proper angle of attack and implementation has significant effect on lift force. Insufficient lift force might cause fail of airplane flying, especially at high speed. Modern technologists use different simulation techniques to avoid costly model testing. But simulation is based on some assumption. Thus practically results are not fully authentic and have a deviation. In this work numerical and experimental investigation of NACA 0015 is studied at different angle of attack (degree) at different velocity of air by determining the forces at every two degrees from 0 0 to 18 0. The experiment is conveyed in a low speed wind tunnel. The numerical analysis is conducted using ANSYS (combined with CFD and FLUENT FLOW). The use of the CFD technology greatly reduces the overall investment and efforts for aerofoil design. CFD method contributes to visualize the flow pattern inside aerofoil and takes less time and comparatively faster than experiment. After completing the experimental, numerical data is compared. Therefore, the objective of this paper is to find the deviation and validation of aerodynamics characteristics of NACA 0015 aerofoil for experimental and numerical method.
Effect of Reynolds Number on the Aerodynamic Performance of NACA0012 Aerofoil
IOP Conference Series: Materials Science and Engineering, 2018
The present work investigates the effect of Reynolds number on NACA0012 aerofoils for various angles of attack on the aerodynamic characteristics both experimentally as well as numerically. The modifications in the flow, as well as aerodynamic characteristics of the NACA0012 aerofoil, are systematically compared using pressure coefficient, lift coefficient, vortex shedding, etc. The study was conducted for a chord wise Reynolds number of (a) 2.21 x 10 5 and (b) 2.81 x 10 5 at an angle of attack of 0 o , 5 o , 10 o , 15 o and 20 o. A large difference in the pressure coefficient is observed between the top and bottom surface in the case of lower Reynolds number and thus it indicates that at low Reynolds number high lift is generated than at high Reynolds number. L/D study also reveals that with increasing Reynolds number the NACA0012 aerofoil losses its lifting aerodynamics property. From the vortex plot, it is clear that leading edge shedding has a negative impact on the lift of the aerofoil for 2D simulation. Thus, this paper sufficiently demonstrates the effect of Reynolds number on the aerodynamic characteristics of the NACA0012 aerofoil.
A Comparative Study of Turbulence Models on Aerodynamics Characteristics of a NACA0012 Airfoil
International Journal of Integrated Engineering, 2018
This paper presented a computational fluid dynamics (CFD) simulation of air flow past a 2D model NACA0012 airfoil at high Reynolds number (Re = 3.0 x 10 6) at various angles of attack (-10 to 15). The simulations were undertaken to inform on how the fluid flowed around the airfoil by solving the steady state governing equations of continuity and momentum conservation that are combined with one of three turbulence models Spalart-Allmaras, Realizable k-ε and k-ω shear stress transport (SST). It is observed that the Realizable k-ε eliminates the small separation bubble on the upper surface of the airfoil and delaying separation flow. Also, for the lift coefficient, CL and drag coefficient, CD investigated in this paper, the predicted data have good agreement with other published data.
Comparison of Aerodynamic Characteristics of NACA 0012 and NACA 2412 Airfoil
International Journal for Research in Applied Science and Engineering Technology, 2021
A comparison between NACA 0012 and NACA 2412 has been made by comparing the lift co- efficient, drag co-efficient, pressure contour and velocity contour at various angles of attack. The process has been done taking steady state flow around NACA-0012 and NACA-2412 airfoil using 1m chord length and a velocity of 88.65m/s. The main aim is to understand the aerodynamic characteristics of both the airfoils at different angles of attack and draw a conclusion on which performs better under the same conditions. Modelling and numerical analysis has been carried out by using commercially available CFD software, which is a convenient method of analysis since computational methods are more preferred to experimental methods due to low expenses involved. The numerical results demonstrated are compatible with those of the theory. This confirms the validity of using Computational Fluid Dynamics (CFD) as a reliable alternative to experimental procedures.
Numerical Simulation of NACA2415 Airfoil: At Different Low Reynolds Numbers and Angles of Attack
2017
This project simulates NACA2415 airfoil on ANSYS Workbench and ANSYS FLUENT at low Reynolds numbers at different angles of attack. This is a 2-D simulation andSpalart-Allmaras is the preferred turbulentmodel solver for this process, it yielded more results closer to experimental results when compared against K-epsilon and other turbulent models.Contours of Pressure and Velocity are presented in this paper with their inferences discussed while Plots of Coefficient of Pressure (CP) about the chord lengths along the airfoil and Coefficient of Lift (CL) are plotted to compare the CFD and the experimental results. Effect of Reynolds number and Angle of Attack is thus studied and investigated.
2020
For better designing of an airfoil, the aerodynamic characteristics of the airfoil need to be investigated both experimentally and numerically. Coefficient of lift (C L), coefficient of drag (C D), variation of C L /C D ratio with angle of attack is very important parameters in CFD analysis. In this study the above parameters are investigated for two symmetric airfoils (NACA0018 and NACA0012) at two different low Reynolds numbers of 300,000 and 700,000. This numerical results show that the stall angle for NACA0018 airfoil at Re=300,000 is less than 17 degree and at Re=700,000 for the same airfoil it is 17.5 degree and this happened due to the increased velocity. C L increases more linearly than C D up to about 10 degree so that C L /C D ratio increases with the angle of attack and then decreases after or near about 10 degree. It has been also found that higher the Reynolds number, greater the value of C L /C D ratio. Besides, it is evident from this simulation that NACA 0012 produces more lift than NACA 0018 for the same Reynolds number. That's why, NACA 0012 airfoil may be verily used for aircraft application whereas NACA 0018 airfoil may be used in VAWT (Vertical Axis Wind Turbine) And HAWT (Horizontal Axis Wind Turbine) to capture the wind energy and convert it to useable energy which is one form of renewable energy.
A comparative CFD analysis of NACA0012 and NACA4412 airfoils
Journal of Energy Systems
Wind energy has been seen as one of the most suitable sources of renewable energy. Wind energy is low cost when compared the other sources. Therefore, wind energy can gain an edge over the fossil-fired power plants. Aerodynamic efficiency of the airfoil is very crucial for aerodynamic efficiency of the wind turbine. The primary purpose of our study was to analyze the NACA0012 and NACA4412 airfoil at various attack angles with constant Reynolds number and to examine the effects of the symmetrical and asymmetrical profiles of the airfoil. Analysis of aerodynamic performance of NACA0012 and NACA4412 airfoil were performed with using ANSYS Fluent program. Also, lift coefficients and drag coefficients were calculated at various attack angles. According to calculations, optimum attack angles were found for each profile. Finally, NACA0012 and NACA4412 airfoils were discussed and reported in terms of their airfoil performances.