Numerical Investigation of NACA-0015 Airfoil Performance Using ANSYS A Detailed Study of Lift, Drag, and Stall Characteristics (original) (raw)
Related papers
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.
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.
5th International Conference on Engineering, Research, Innovation and Education (ICERIE), 2019
Study of a two-dimensional CFD analysis is done to investigate the effects of angle of attack and Mach number on the aerodynamic characteristics of NACA (National Advisory Committee for Aeronautics) 0012 airfoil considering turbulent flow around it. Different parameters used, and its effects, in analysis like domain shape, grid cells, number of nodes in meshing, various boundary conditions are surveyed. Change in Reynolds number of fluid results in different output, hence the variation of lift & drag coefficient with the change in Reynolds number is analyzed. To show the behavior of the airfoil at these conditions is the main objective of this paper. The simulation is done in ANSYS Fluent and both the k-omega and k-epsilon turbulence modeling method was used to compare the results. From the CL (life Coefficient)/ CD (Drag Coefficient) ratio, it shows that when the Mach number (M) increases, CL increases but CD remains constant at different operating conditions. Moreover, it is observed that the CL/CD ratio decreases because of a rapid downward for the CL and an abrupt upward for the CD with velocity approaching the sonic velocity. Computational results are validated with the results of NASA Langley Research Center validation cases.
LIFT AND DRAG PERFORMANCE OF NACA0012 AIRFOIL AT VARIOUS ANGLE OF ATTACK USING CFD
In this paper, an expansion of my research work [1] we complete a numerical investigation of lift and drag performance of the NACA0012 airfoil at a different negative and positive angle utilizing computational fluid dynamic. This investigation of the two dimensional (2D) subsonic fluid flow over an airfoil at an alternate approach extending from negative angle-6 degree to positive point 10 degrees (distinction of 2 degrees AoA) at consistent Mach number is available. For this testing and investigation, we utilized a model of K-ω SST turbulence. The final product of the analysis, computational fluid dynamic reenactment demonstrates the applicability to the energizing finding the literature. Through this testing, we are communicating a dependable option test technique for discovering coefficient of drag and lift.
RANS Simulations of Aerodynamic Performance of NACA 0015 Flapped Airfoil
Fluids, 2017
An analysis of 2D subsonic flow over an NACA 0015 airfoil with a 30% trailing edge flap at a constant Reynolds number of 10 6 for various incidence angles and a range of flap deflections is presented. The steady-state governing equations of continuity and momentum conservation are solved combined with the realizable k-ε turbulence model using the ANSYS-Fluent code (Version 13.7, ANSYS, Inc., Canonsburg, PA, USA). The primary objective of the study is to provide a comprehensive understanding of flow characteristics around the NACA 0015 airfoil as a function of the angle of attack and flap deflection at Re = 10 6 using the realizable k-ε turbulence model. The results are validated through comparison of the predictions with the free field experimental measurements. Consistent with the experimental observations, the numerical results show that increased flap deflections increase the maximum lift coefficient, move the zero-lift angle of attack (AoA) to a more negative value, decrease the stall AoA, while the slope of the lift curve remains unchanged and the curve just shifts upwards. In addition, the numerical simulations provide limits for lift increment ∆C l and C l, max values to be 1.1 and 2.2, respectively, obtained at a flap deflection of 50 •. This investigation demonstrates that the realizable k-ε turbulence model is capable of predicting flow features over an airfoil with and without flap deflections with reasonable accuracy.
CFD Analysis of a Naca 0009 Aerofoil at a Low Reynolds Number
2021
Proper blade design, selection and use continue to gain importance with the developing technology, aviation and space industry. Many applications use wings such as aircraft (planes, helicopters, etc.), UAV (Unmanned Aerial Vehicle), wind turbines and so on. This study covers a NACA 0009 profiled wing with a 111 mm span and chord and its CFD analysis using Ansys version 15.0. Three-dimensional analysis has been done using Ansys Fluent. A geometry was created, this geometry was meshed properly, tighter especially close to the wings, and its analysis was completed using the k-w turbulence model. In total 2,078,272 nodes and 2,036,295 elements have been formed in the mesh. Four different angles of attack have been tested which are 0°, 5°, 10° and 15° at 37,000 Reynolds number. Generated mesh has an average skewness rate of 1.3 and an average orthogonal quality rate of 0.97. Velocity contours and streamlines have been compared to the literature. Lift and drag coefficients have been monit...
Maǧallaẗ al-baṣraẗ li-l-ʻulūm al-handasiyyaẗ, 2023
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.
Journal of Mechatronics and Automation, 2019
Aircraft post-flight reduction is one of the most important research topics, since postreduction is effective in all parameters of bird performance, such as maximum speed, fast acceleration, shortening the runway required, high maneuverability, and reduced fuel consumption. Therefore, it is important to examine how the force applied to the airfoil changes in different streams from an industrial point of view. In this study, NACA(National Advisory Committee for Aeronautics) Airfoil 0012 has been studied. Numerical solution is used for the study. In the simulations, the air fluid and Mach number 0.5 are considered and the lift, drag and pressure coefficients at different attack angles are investigated. The results show that this airfoil has a lift factor of 0 due to its symmetric geometry at angle of attack 0 but its drag coefficient is about 0.01384 and its pressure coefficient is about-0.483. By varying the angle of attack from-12 to +12, it was observed that for the positive attack angle the lift coefficient increases and for the negative attack angle increases the lift coefficient decreases. Also with increasing angle of attack the drag coefficient always increases and the coefficient of pressure coefficient decreases.
Computational Study of Aerodynamic Flow over NACA 4412 Airfoil
British Journal of Applied Science & Technology
The lift and drag coefficient plots for any airfoil provides a means for measuring its aerodynamic characteristics. These are very useful in deciding if a particular airfoil is appropriate for any particular application area. This study computationally predicts how the lift coefficient, drag coefficient and drag polar derived for the aerodynamic flow over the NACA 4412 airfoil vary with angles of attack. The effect of varying Reynolds number on the aerodynamic characteristics was also investigated. The finite-volume based computational fluid dynamics code; ANSYS Fluent was used to solve the continuity equation, the Reynolds Averaged Navier-Stokes equation and the turbulence transport equations governing the flow. For the range of Reynolds number considered, flow was taken as incompressible, steady and two-dimensional. Simulations were run for angles of attack ranging from-10° to 18° with an interval of 2° and for a Reynolds number range of 1.0 x 10 6 to 13.0 x 10 6. Results at a given Reynolds number revealed a steady variation between lift coefficient and angle of attack within the pre-stall region and a gradually increasing curve for the drag coefficients. A constant stalling angle at 14° w ith gradually increasing value for the maximum lift coefficient was recorded as the Reynolds number increased. The drag polar was also found to be constant at 6° for all the ranges of R eynolds number. The results obtained showed that numerically solving for flow problems is a valid approach for obtaining the aerodynamic characteristics of an airfoil since the results were compared with data from wind tunnel tests.
Numerical Analysis and Comparison on Aerodynamics Characteristics on NACA-0012 & NACA-4412
The numerical analysis of the two dimensional subsonic flow over a NACA 0012 & NACA 4412 airfoil at various angles of attack which is operating at a Reynolds number of 3×10 6 is presented. A commercial computational fluid dynamic (CFD) code ANSYS FLUENT based on finite volume technique is used for the calculation of aerodynamics performance. The two dimensional model of the airfoil and the mesh is created through ANSYS Meshing which is run in Fluent for numerical iterate solution. The steady-state governing equations of Reynolds averaged Navier -Stokes is calculated for analyzing the characteristics of two-dimensional airfoils and the realizable k-epsilon model with Enhanced wall treatment is adopted for the turbulence closure. The aim of the work is to show the behavior of the airfoil at these conditions and to compare the aerodynamics characteristics between NACA 0012 & NACA 4412 such as lift co-efficient, drag co-efficient and surface pressure distribution over the airfoil surface for a specific angle of attack. Calculations were done for constant air velocity altering only the angle of attack for every airfoil model tested. This analysis can be used for the wing design and other aerodynamic modeling correspon ds to these airfoil.