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Artykuły w czasopismach na temat „NACA0012”

Autor: Grafiati

Data publikacji: 3 czerwca 2025

Data aktualizacji: 31 lipca 2025

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1

Zhao, Liangyu, and Shuxing Yang. "Influence of Thickness Variation on the Flapping Performance of Symmetric NACA Airfoils in Plunging Motion." Mathematical Problems in Engineering 2010 (2010): 1–19. http://dx.doi.org/10.1155/2010/675462.

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In order to investigate the impact of airfoil thickness on flapping performance, the unsteady flow fields of a family of airfoils from an NACA0002 airfoil to an NACA0020 airfoil in a pure plunging motion and a series of altered NACA0012 airfoils in a pure plunging motion were simulated using computational fluid dynamics techniques. The “class function/shape function transformation“ parametric method was employed to decide the coordinates of these altered NACA0012 airfoils. Under specified plunging kinematics, it is observed that the increase of an airfoil thickness can reduce the leading edge

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2

Yawara, Eka, Yohannes Agus Jayatun, and Daru Sugati. "Pengaruh Profil Sudu Terhadap Koefisien Daya Turbin Gorlov." KURVATEK 1, no. 2 (2017): 7–11. http://dx.doi.org/10.33579/krvtk.v1i2.235.

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Masalah keterbatasan penyediaan sumber energi dari energi fosil diatasi dengan optimalisasi sumber energi terbarukan, misalnya sumber daya dari air. Salah satu kendala yang dihadapi dari penyediaan pembangkit daya air berskala besar adalah problem lingkungan. Oleh karena itu pembangkit daya air skala kecil atau mikro terus diupayakan pengembangannya, misalnya penggunaan Turbin Gorlov yang memanfaatkan potensi air dengan head rendah atau sangat rendah. Pada penelitian ini dilakukan studi pengaruh profil sudu terhadap koefisien daya pada Turbin Gorlov. Penelitian dilakukan dengan cara simulasi m

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3

Sutikno, Priyono, Yuliandra Syahrial Nurdin, Doddy Risqi, Eki Mardani, and Erpinus Sihombing. "Experimental of Three Parallel Water Current Turbine with Optimized Straight Blades and Using Flow Concentrator Channeling Device to Augmented Performance and Self-Starting Capability." Applied Mechanics and Materials 758 (April 2015): 153–58. http://dx.doi.org/10.4028/www.scientific.net/amm.758.153.

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Water current turbine with vertical blade can be used on the river flow, ocean current or tidal current. The three parallel turbines with 40 degree azimuth different, have advantages doubling the power output and diminish the torque fluctuation. When the turbine equipped by the concentrator channeling device, the performance increased and the self-starting capability also augmented. During the experiments is indicated the flow phenomenon behind the turbine, the vortex formation created additional head or formation of low hydraulic level and facilitate the turbine coefficient of power produced

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4

Syafei, M. Hilman Gumelar, Ragil Tri Indrawati, and Tanwir Ahmad Farhan. "Implementation of the Airfoil parameterization PARSEC Method in Python." Jurnal Rekayasa Mesin 17, no. 3 (2022): 485. http://dx.doi.org/10.32497/jrm.v17i3.4000.

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<p>Airfoil telah mengalami banyak perkembangan dan optimalisasi melalui berbagai cara. Terdapat berbagai teknik yang dapat digunakan untuk memodifikasi bentuk arifoil standar yang ada saat ini. Metode PARSEC merupakan salah satu teknik parameterisasi yang paling banyak digunakan untuk memodifikasi bentuk airfoil. Paper ini menyediakan penjelasan yang komprehensif.mengenai implementasi metode PARSEC pada bahasa pemrograman <em>python</em>. Studi ini menggunakan Airfoil standar jenis NACA0012 sebagai referensi untuk mengevaluasi metode PARSEC. Airfoil NACA0012 yang dihasilkan d

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5

Jiang, Zhongyuan, Jiangming Ding, and Zhourui Li. "Study on the Impact of Tail Wing Profiles on the Resistance Characteristics of Amphibious Vehicles." Journal of Marine Science and Engineering 12, no. 5 (2024): 780. http://dx.doi.org/10.3390/jmse12050780.

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The resistance performance of amphibious vehicles can be improved by installing underwater tail hydrofoils. The research on the impact of different hydrofoil profiles on the resistance characteristics of amphibious vehicles can provide a reference for the vehicle’s design. For an amphibious vehicle model, five shapes of symmetrical hydrofoils, NACA0012, NACA0015, NACA0016, and asymmetric hydrofoils NACA23012, NACA66-209, were selected as the underwater tail wing of the vehicle body, respectively. Based on the RANS method and overset grid technology, the resistance performance of the vehicle bo

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6

Ghadimi, Parviz, Saman Kermani, and Mohammad A. Feizi Chekab. "Numerical Hydroacoustic Analysis of NACA Foils in Marine Applications and Comparison of Their Acoustic Behavior." ISRN Mechanical Engineering 2013 (July 30, 2013): 1–12. http://dx.doi.org/10.1155/2013/714363.

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One of the most important parameters to be considered in the design process of lifting surfaces for marine applications is the acoustic noise emitted by the designed surface. In the present work, the hydroacoustic fields of NACA0012 and NACA0018 hydrofoils are calculated, and the acoustic behavior of these sections is examined and compared at different angles of attack. The Ansys-CFX Navier-Stokes solver is used for hydrodynamic analysis, and a highly accurate multithread program named ACOPY is developed in Python programming language based on the Ffowcs Williams and Hawkings method for acoust

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7

Lam, K., Y. F. Lin, Y. Liu, and L. Zou. "Numerical Investigation of Flow past a Wavy Airfoil." Applied Mechanics and Materials 110-116 (October 2011): 4269–75. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.4269.

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The effect of the wavy surface on the aerodynamic characteristics of an airfoil is studied using the large eddy simulations. A more gentle lift characteristic is obtained during stall. For angles of attack less than the baseline stall angle of a NACA0012 airfoil, a lift coefficient reduction was observed for the wavy airfoils, while the lift coefficient increases up to 23% greater than that of a NACA0012 airfoil when the angle of attack is larger than the baseline stall angle of the NACA0012 airfoil.

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8

Taslin, Puteri Nurfarah Adawiyah, Aliashim Albani, Mohd Zamri Ibrahim, Mohd Azlan Musa, Zulkifli Mohd Yusop, and Mohd Afifi Jusoh. "Computational Fluid Dynamics Analysis of Seven Selected Hydrofoils for Different Angle of Attack." Jurnal Kejuruteraan si4, no. 1 (2021): 71–75. http://dx.doi.org/10.17576/jkukm-2021-si4(1)-09.

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This paper aims to conduct a Computational fluid dynamics (CFD) analysis of seven selected hydrofoils at different angles of attack (AOA) for application in ocean current energy converter blades. The hydrofoil models are NACA0012, NACA0015, NACA2412, NACA2414, NACA2415, NACA 4412, and E387. The geometry was managed using the Design Modeler tool. The fluid flow simulation was carried out using ANSYS Fluent. The result showed the performance of E387 is betterthan other hydrofoils asit gives betterlift force with the least drag force,resulting in better hydrodynamics of turbine blade. Overall, th

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9

Lee, Seongkyu. "The Effect of Airfoil Shape on Trailing Edge Noise." Journal of Theoretical and Computational Acoustics 27, no. 02 (2019): 1850020. http://dx.doi.org/10.1142/s2591728518500202.

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This paper investigates the effect of airfoil shape on trailing edge noise. The boundary layer profiles are obtained by XFOIL and the trailing edge noise is predicted by a TNO semi-empirical model. In order to investigate the noise source characteristics, the wall pressure spectrum is decomposed into three components. This decomposition helps in finding the dominant source region and the peak noise frequency for each airfoil. The method is validated for a NACA0012 airfoil, and then five additional wind turbine airfoils are examined: NACA0018, DU96-w-180, S809, S822 and S831. It is found that t

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10

Lv, Hongqing, Zhenqing Wang, Jiahao Chen, and Lei Xu. "The Influence of Boundary Layer Caused by Riblets on the Aircraft Surface." Applied Sciences 10, no. 11 (2020): 3686. http://dx.doi.org/10.3390/app10113686.

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Drag reduction of riblets is one of the most important problems in drag reduction of non-smooth surfaces. In the past two decades, the use of riblets arranged along the flow direction to reduce frictional resistance has received considerable attention. In this paper, we study the plates with the triangular concave grooves, triangular protrusion riblets, trapezoidal concave grooves, trapezoidal protrusion riblets, and circular concave grooves. The numerical simulation method is used to calculate five kinds of plates with grooves and riblets under multiple working conditions. The results showed

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11

Silva Maffei, Felipe, Gabriel Angelo, Silvia Maria Stortini González Velázquez, Sergio Luis Rabelo de Almeida, Jorge Alexandre Onoda Pessanha, and Edvaldo Angelo. "Numerical Analysis of a Flow over a Naca0015 Airfoil Containing the Flap and Gurney Flap Elements." International Journal of Scientific Research and Management 10, no. 01 (2022): 731–46. http://dx.doi.org/10.18535/ijsrm/v10i1.ec03.

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The present work aimed at numerical simulation of a two-dimensional, incompressible and steady-state airflow over a NACA0015 airfoil with flap and Gurney flap using the standard turbulence models k-epsilon, k-omega and versions of these models with modified constants. All meshes used were structured. Comparison of the results of the turbulence models with experimental data from the literature shows differences between the results in the leading-edge region. The differences were minimized by adjusting the contents of the turbulence models. For validation, the k-epsilon turbulence model with mod

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12

Raghunathan, S., R. D. Mitchell, and M. A. Gillan. "Transonic shock oscillations on NACA0012 aerofoil." Shock Waves 8, no. 4 (1998): 191–202. http://dx.doi.org/10.1007/s001930050113.

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13

Rudresh, M., S. Rohith, T. N. Rohith, R. Darshan, and H. V. Dilip. "Aerodynamic Optimization of Wing by Camber Morphing using Cfd." International Journal of Engineering and Advanced Technology (IJEAT) 9, no. 5 (2020): 122–30. https://doi.org/10.35940/ijeat.E9396.069520.

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This paper presents the CFD analysis of the 2-Dimensional NACA0012 airfoil carried out for identifying its aerodynamic coefficients (Lift and Drag coefficients), then further implementing morphing technology on the same two-dimensional NACA0012 airfoil, again carrying out CFD analysis to determine its aerodynamic coefficients (Lift coefficient (CL) and Drag coefficient (CD), then comparing the results of both the airfoil shapes particularly to the amount of Lift generated to prove that morphing airfoil produces more amount of Lift when compared to typical airfoil shapes. Using ANSYS Design mod

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14

ENOMOTO, Shunji, Hiroyuki KATO, Hiroki URA, Yuzuru YOKOKAWA, and Kazuomi YAMAMOTO. "Large Eddy Simulation of NACA0012 wing tip vortices." Proceedings of the Fluids engineering conference 2004 (2004): 191. http://dx.doi.org/10.1299/jsmefed.2004.191.

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15

Açıkel, Halil Hakan, Melike Tosun, Mustafa Serdar Genç, and Kemal Koca. "Numerical investigation on NACA0012 airfoil with tubercular structure." EPJ Web of Conferences 269 (2022): 01001. http://dx.doi.org/10.1051/epjconf/202226901001.

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Humpback whales have very special fins, which reduce the friction force by the projections on the fins and enhance the lift force with increasing angle of attack. Thus, it has opportunity to move with less energy. In this study, the tubular structure was formed and adapted to the NACA0012 airfoil profile. Numerical modelling of tubercle wing was performed in ANSYS FLUENT. In numerical modelling, k-ω SST and Transition SST turbulence models were used to investigate tubercle wing performance. The tubercle structure on the wing provided to canalize the flow in the tubercle cavities, thus flow sep

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16

Dass, Lakshuman, Anas Abdul Rahman, Kumaran Rajendran, and Gisrina Elin Suhri. "Numerical analysis of wake turbulence between hybrid tidal turbine and hypothetical actuator cylinder for shallow water with low velocity conditions." Journal of Mechanical Engineering and Sciences 16, no. 1 (2022): 8673–90. http://dx.doi.org/10.15282/jmes.16.1.2022.03.0686.

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Towards modernisation of the technological era, electricity demands have been an issue. Although the supply of electrical energy from the renewable sources are increasing, it is still not sufficient to offset the carbon production. Malaysia as a developing country needs ample of supply of electrical energy. As most of the current electrical energy for the country are being produced by non renewable sources, the Malaysian government have started looking into renewable options to produce electrical energy. There are various sources of energy that are available in Malaysia such as solar, natural

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17

Caicedo, Edison H., and Muhammad S. Virk. "Numerical Study of NACA 0012 Aeroacoustics Response for Normal and Icing Conditions." Applied Mechanics and Materials 875 (January 2018): 89–93. http://dx.doi.org/10.4028/www.scientific.net/amm.875.89.

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This paper describes a multiphase computational fluid dynamics (CFD) based numerical study about aeroacoustics response of NACA0012 airfoil for both normal and icing conditions. Three different turbulence models (RANS, DES & LES) are tested where Detached Eddy simulation (DES) turbulence modelling approach is found suitable for this case study. Aeroacoustics numerical results for clean NACA 0012 are compared with the experimental data obtained from NASA report 1218 [1], where a good agreement is found. An extended CFD study is carried out for iced NACA 0012 airfoil, where results show more

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18

Peng, Zhi Ling. "Flow Field Simulation of Airfoil and Analysis of Vibration Modal Based on ANSYS." Advanced Materials Research 268-270 (July 2011): 581–83. http://dx.doi.org/10.4028/www.scientific.net/amr.268-270.581.

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By taking NACA0012 airfoil as the research object，the pressure distribution is given，based on the simulation of airfoil fieldflow field with ANSYS. Each modal characteristic is visually display ，by analysis on vibration modal of airfoil

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19

Mula, Ayat, and Mohammed Abdulwahid. "Numerical Simulation of the Aerodynamic Characteristics of NACA0012 Airfoil Based on Operational Parameters." Basrah journal for engineering science 23, no. 1 (2023): 81–89. http://dx.doi.org/10.33971/bjes.23.1.11.

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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 be

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20

Bhogle, Prathmesh. "Performance Testing of NACA0012 Aerofoil by Providing Dimple Surface." International Journal for Research in Applied Science and Engineering Technology V, no. IV (2017): 1284–87. http://dx.doi.org/10.22214/ijraset.2017.4229.

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21

OHTAKE, Tomohisa. "Flow Field around NACA0012 Airfoil in Low Reynolds Numbers." JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 64, no. 2 (2016): 123–30. http://dx.doi.org/10.2322/jjsass.64.123.

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22

OHTAKE, Tomohisa, and Tatsuo MOTOHASHI. "Flow Field around NACA0012 Airfoil at Low Reynolds Numbers." JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 57, no. 669 (2009): 397–404. http://dx.doi.org/10.2322/jjsass.57.397.

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23

IMAMURA, Taro, Shunji ENOMOTO, and Kazuomi YAMAMOTO. "Noise Simulation around NACA0012 Wingtip using Large Eddy Simulation." TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 55, no. 4 (2012): 214–21. http://dx.doi.org/10.2322/tjsass.55.214.

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24

Goto, Naoki, Hideaki Suetsuna, Makoto Iida, and Chuichi Arakawa. "1205 NOISE ANALYSIS OF NACA0012 TRAIKING EDGE USING LES." Proceedings of the Fluids engineering conference 2009 (2009): 387–88. http://dx.doi.org/10.1299/jsmefed.2009.387.

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25

Naeem, Samara Munaem. "Structural and Stress Analysis of NACA0012 Wing Using SolidWorks." Mathematical Modelling of Engineering Problems 11, no. 8 (2024): 2181–86. http://dx.doi.org/10.18280/mmep.110820.

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26

Karim, Md Mashud, and Mohammad Shakil Ahmmed. "Numerical study of periodic cavitating flow around NACA0012 hydrofoil." Ocean Engineering 55 (December 2012): 81–87. http://dx.doi.org/10.1016/j.oceaneng.2012.06.034.

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27

Rodríguez, I., O. Lehmkuhl, R. Borrell, and A. Oliva. "Direct numerical simulation of a NACA0012 in full stall." International Journal of Heat and Fluid Flow 43 (October 2013): 194–203. http://dx.doi.org/10.1016/j.ijheatfluidflow.2013.05.002.

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28

Yemenici, Onur. "Experimental Investigation of the Flow Field around NACA0012 Airfoil." International Journal of Sciences Volume 2, no. 2013-08 (2013): 98–101. https://doi.org/10.5281/zenodo.3348422.

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In this study, an experimental investigation of the flow field around NACA0012 airfoil was carried out in a wind tunnel under the effects of the Reynolds number and angle of attack. The Reynolds number based on the chord length of airfoil and the attack angle was varied from 9.7x104 to 1.9x105 and 0 to 140 respectively. Mean velocities were measured by a constant temperature anemometer and static pressures by a micro-manometer. The results showed that the pressure and lift coefficients displayed a strong dependence on Reynolds number and attack angle.Read Complete Article at ijSciences: V22013

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29

Le, Nam Tuan Phuong, Ngoc Anh Vu, Le Tan Loc, and Tran Ngoc Thoai. "New temperature jump boundary condition in high-speed rarefied gas flow simulations." Vietnam Journal of Mechanics 39, no. 2 (2017): 165–76. http://dx.doi.org/10.15625/0866-7136/8760.

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The effect of the sliding friction has been important in calculating the heat flux of gas flow from the surface since there is some slip over the surface. There has not been any the temperature jump condition including the sliding friction part so far. In this paper, we will propose a new temperature jump condition that includes the sliding friction. Our new temperature jump condition will be evaluated for NACA0012 micro-airfoil in high-speed rarefied gas flow simulations using the CFD method, which solves the Navier-Stokes equations within the OpenFOAM framework with working gas as air. The a

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30

Sun, Zhaozheng, and Wenhui Yan. "Comparison of Different Turbulence Models in Numerical Calculation of Low-Speed Flow around NACA0012 Airfoil." Journal of Physics: Conference Series 2569, no. 1 (2023): 012075. http://dx.doi.org/10.1088/1742-6596/2569/1/012075.

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Abstract To further develop a more effective turbulence model and improve the calculation accuracy of the flow, a new turbulence model was constructed using the deformation rate tensor, grouping the average. Due to the need to evaluate the applicability of the new turbulence model in the numerical calculation, the flow around the NACA0012 airfoil with a Mach number of 0.15 and multiple angles of attack was calculated on the OpenFOAM calculation platform based on grid independence research. The Spalart-Allmaras (S-A) model and the newly proposed turbulence model were adopted. The surface pressu

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31

Abdus, Shabur, Hasan Afnan, and Ali Mohammad. "Comparison of Aerodynamic Behaviour between NACA 0018 and NACA 0012 Airfoils at Low Reynolds Number Through CFD Analysis." Advancement in Mechanical Engineering and Technology 3, no. 2 (2020): 1–8. https://doi.org/10.5281/zenodo.4003677.

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<em>For better designing of an airfoil, the aerodynamic characteristics of the airfoil need to be investigated both experimentally and numerically. Coefficient of lift (C<sub>L</sub>), coefficient of drag (C<sub>D</sub>), variation of C<sub>L</sub>/C<sub>D</sub> 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

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32

Kouser, Taiba, Yongliang Xiong, Dan Yang, and Sai Peng. "Direct Numerical Simulations on the three-dimensional wake transition of flows over NACA0012 airfoil at Re = 1000." International Journal of Micro Air Vehicles 13 (January 2021): 175682932110556. http://dx.doi.org/10.1177/17568293211055656.

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For micro air vehicles (MAV), the precise prediction of aerodynamic force plays an important role. The aerodynamic force of a comparative low Reynold number (Re) vehicle tends to be affected by the different flow modes. In this paper, the aerodynamic performance of a three-dimensional NACA0012 airfoil is studied numerically. A range of angles of attack ( α) 0°−25° and Reynolds number 1000 is considered. Mean and fluctuating coefficients of aerodynamic forces around NACA0012 airfoil are analyzed for different wake modes. The difference of aerodynamic forces between two and three-dimensional sim

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33

Bucur, I. O., D. E. Crunteanu, and M. C. Dombrovschi. "Numerical Analysis of Tilted Cavities Placement Effects on the Airfoils in Wind Turbine Systems." IOP Conference Series: Earth and Environmental Science 1375, no. 1 (2024): 012018. http://dx.doi.org/10.1088/1755-1315/1375/1/012018.

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Abstract The objective of this study is to contribute to the research and development of vertical axis wind turbines (VAWTs). This will be achieved through a comprehensive analysis of modified airfoils featuring inclined cavities, specifically tailored for applications in wind systems but not limited to this. The investigation conducted in this manuscript utilizes computational fluid dynamics (CFD) to perform a numerical assessment of different airfoil configurations that have undergone modifications consisting of the incorporation of tilted cavities along distinct lengths of their upper surfa

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34

Li, Juan, and Zi-Niu Wu. "Vortex force map method for viscous flows of general airfoils." Journal of Fluid Mechanics 836 (December 11, 2017): 145–66. http://dx.doi.org/10.1017/jfm.2017.783.

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In a previous paper, an inviscid vortex force map approach was developed for the normal force of a flat plate at arbitrarily high angle of attack and leading/trailing edge force-producing critical regions were identified. In this paper, this vortex force map approach is extended to viscous flows and general airfoils, for both lift and drag forces due to vortices. The vortex force factors for the vortex force map are obtained here by using Howe’s integral force formula. A decomposed form of the force formula, ensuring vortices far away from the body have negligible effect on the force, is also

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35

El Maani, Rabii, Soufiane Elouardi, Bouchaib Radi, and Abdelkhalak El Hami. "Multiobjective aerodynamic shape optimization of NACA0012 airfoil based mesh morphing." International Journal for Simulation and Multidisciplinary Design Optimization 11 (2020): 11. http://dx.doi.org/10.1051/smdo/2020006.

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The actual use of computational fluid dynamics (CFD) by aerospace companies is the trade-off result between the perceived costs and benefits. Computational costs are restricted to swamp the design process even if the benefits are widely recognized. The need for fast turnaround, counting the setup time, is also crucial. CFD integrates mathematical relations and algorithms to analyze and solve fluid flow problems. CFD analysis of an airfoil produces results such as the lift and drag forces that determine the performance of an airfoil. Thus, optimizing these aerodynamic performances has proved ex

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36

INOUE, Naoki, and Akira MATSUMOTO. "Wake flow measurements of NACA0012 airfoil at low Reynolds numbers." Proceedings of Conference of Kanto Branch 2002.8 (2002): 501–2. http://dx.doi.org/10.1299/jsmekanto.2002.8.501.

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SAITO, Ryo, Takayuki YAMAGATA, and Nobuyuki FUJISAWA. "Influence of Inflow Turbulence on Discrete Frequency Noise of NACA0012." Proceedings of Conference of Hokuriku-Shinetsu Branch 2017.54 (2017): A032. http://dx.doi.org/10.1299/jsmehs.2017.54.a032.

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38

Cao, Yi, and Shu-Jie Li. "Anisotropic capturing of compressible boundary layer flows over NACA0012 airfoil." Journal of Physics: Conference Series 3042, no. 1 (2025): 012012. https://doi.org/10.1088/1742-6596/3042/1/012012.

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Abstract Accurately capturing the anisotropic features of boundary layers is of great importance in predicting force coefficients of external flows, which requires numerical methods to be accurate and efficient. To this end, we propose algebraically anisotropic numerical methods within a modal discontinuous Galerkin (DG) framework. In our approach, anisotropic basis functions aligned with the principal axes of inertia in each cell are proposed, enabling the capturing of flow features in the normal direction of boundary layers. To guide the anisotropic refinement, we introduce an anisotropic er

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Yossri, Widad, Samah Ben Ayed, and Abdessattar Abdelkefi. "High-Fidelity Modeling and Investigation on Blade Shape and Twist Angle Effects on the Efficiency of Small-Scale Wind Turbines." Energies 16, no. 8 (2023): 3430. http://dx.doi.org/10.3390/en16083430.

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A high-fidelity analysis is carried out in order to evaluate the effects of blade shape, airfoil cross-section. as well as twist angle distribution on the yielded torque and generated power of a horizontal axis Small-Scale Wind Turbine (SSWT). A computational modeling and an effective design for a small turbine with a blade length of 25 cm subject to a 4 m/s freestream velocity are presented, in which a segregated RANS solver is utilized. Four airfoil profiles are assessed, namely NACA0012, NACA0015, NACA4412, and NACA4415, and two blade shape configurations, rectangular and tapered, are evalu

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Han, Rong, Wei Liu, Xiao-Liang Yang, and Xing-Hua Chang. "Effect of NACA0012 Airfoil Pitching Oscillation on Flow Past a Cylinder." Energies 14, no. 17 (2021): 5582. http://dx.doi.org/10.3390/en14175582.

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The flow past a cylinder is a classical problem in flow physics. In a certain range of Reynolds number, there will be Karman vortex street phenomenon in the wake of a cylinder, which will greatly increase the pressure drag of the cylinder. By controlling the vortex shedding phenomenon, drag reduction of the cylinder could be effectively realized. In this paper, a NACA0012 airfoil with pitching oscillation is placed downstream of the cylinder. Based on the tight coupling method, kinematics equations and Navier–Stokes equations in the arbitrary Lagrangian–Eulerian form are solved. Firstly, the e

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Li, Bowen, Qiangqiang Sun, Dandan Xiao, and Wenqiang Zhang. "Numerical Investigation of the Aerofoil Aerodynamics with Surface Heating for Anti-Icing." Aerospace 9, no. 7 (2022): 338. http://dx.doi.org/10.3390/aerospace9070338.

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The aerodynamics of an aerofoil with surface heating was numerically studied with the objective to build an effective anti-icing strategy and balance the aerodynamics performance and energy consumption. NACA0012, RAE2822 and ONERA M6 aerofoils were adopted as the test cases and the simulations were performed in the subsonic flight condition of commercial passenger aircraft. In the first session, the numerical scheme was firstly validated with the experimental data. A parametric study with different heating temperatures and heating areas was carried out. The lift and drag coefficients both drop

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Douvi, Eleni C., and Dionissios P. Margaris. "Aerodynamic Performance Investigation under the Influence of Heavy Rain of a NACA 0012 Airfoil for Wind Turbine Applications." International Review of Mechanical Engineering (IREME) 6, no. 6 (2012): 1228–35. http://dx.doi.org/10.15866/ireme.v6i6.20761.

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The study of the prediction of the flow field and aerodynamic characteristics of a NACA0012 airfoil in simulated heavy rain, using a computational fluid dynamics code is presented. The simulation of rain is accomplished by using the two-phase flow Discrete Phase Model, which is available in the CFD code. Spherical particles are tracked through the two-dimensional, incompressible air flow field over a NACA0012 airfoil, at a simulated rain rate of 1000 mm/h and operating at Reynolds numbers Re=1×106 and Re=3×106. To validate the CFD developed model, the results are compared with well-established

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Tahani, Mojtaba, Mehran Masdari, Hamidreza Eivazi, and Massoud Tatar. "Assessment of turbulence models for transonic oscillating airfoil." International Journal of Numerical Methods for Heat & Fluid Flow 27, no. 11 (2017): 2603–28. http://dx.doi.org/10.1108/hff-04-2016-0142.

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Purpose This paper aims to investigate numerical solution of transonic flow around NACA0012 airfoil under sinusoidal pitch oscillation. Accordingly, effects of the amplitude and frequency of oscillations on aerodynamic coefficients are evaluated and the efficiency of the turbulent models, K-ω shear-stress transport (SST), scale adaptive simulation (SAS) and delayed detached eddy simulation (DDES), in simulation of the nonlinear phenomena – i.e. the interaction between shock and boundary layer and the shock oscillations – is studied. Design/methodology/approach K-ω SST, SAS and DDES models are

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R., Allocious Britto Rajkumar, Mohammed Raffic N., K. Ganesh Babu Dr., and Vignesh V. "Comparative Study on Effective Turbulence Model for NACA0012 Airfoil using Spalart – Allmaras as a Benchmark." International Journal of Trend in Scientific Research and Development 4, no. 3 (2020): 1049–56. https://doi.org/10.5281/zenodo.3892853.

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The present work is dedicated to conduct a comparative study on identifying the effective turbulence model in terms of flow outlet velocity, error percentage, number of iterations and time coefficient using NACA0012 airfoil by considering Spalart â€“ Allmaras as a reference model. The current study considers 12 different turbulence models including Spalart â€“ Allmaras for obtaining the output characteristics individually. The turbulence models in existence such as Standard K epsilon, RNG K epsilon, Realizable variant of K epsilon, Standard K Omega, SST K Omeg

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Hasegawa, Hiroaki, and Shigeru Obayashi. "Active Stall Control System on NACA0012 by Using Synthetic Jet Actuator." Journal of Flow Control, Measurement & Visualization 07, no. 01 (2019): 61–72. http://dx.doi.org/10.4236/jfcmv.2019.71005.

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Shi, Zhouhao, Zhanshan Xie, Weidong Shi, Qinghong Zhang, and Lingwei Tan. "Numerical Investigation on Cavitation Suppression of Microchannel over a NACA0012 Hydrofoil." Shock and Vibration 2021 (March 30, 2021): 1–10. http://dx.doi.org/10.1155/2021/6641839.

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To find a better method to suppress cavitation, a microchannel design connecting the internal low-pressure area with the outside is proposed for the first time in this paper; the method was adopted to replenish fluid in the interior of the low-pressure area to inhibit cavitation. Through numerical simulation, it is found that the size and position of microchannel have a certain influence on the cavitation inhibition. The results show that the generation and development of cavitation, under the same working conditions, can be effectively restrained by adopting appropriate microchannel (x = 0.05

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Camacho, Emanuel, Fernando Neves, André Silva, and Jorge Barata. "Numerical Investigation of Frequency and Amplitude Influence on a Plunging NACA0012." Energies 13, no. 8 (2020): 1861. http://dx.doi.org/10.3390/en13081861.

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Natural flight has always been the source of imagination for Mankind, but reproducing the propulsive systems used by animals that can improve the versatility and response at low Reynolds number is indeed quite complex. The main objective of the present work is the computational study of the influence of the Reynolds number, frequency, and amplitude of the oscillatory movement of a NACA0012 airfoil in the aerodynamic performance. The thrust and power coefficients are obtained which together are used to calculate the propulsive efficiency. The simulations were performed using ANSYS Fluent with a

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Jha, Shailesh, Uddipta Gautam, S. Narayanan, and LA Kumaraswami Dhas. "Effect of Reynolds Number on the Aerodynamic Performance of NACA0012 Aerofoil." IOP Conference Series: Materials Science and Engineering 377 (June 2018): 012129. http://dx.doi.org/10.1088/1757-899x/377/1/012129.

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ITGEL, Uguumur, Hiroaki HASEGAWA, and Shigeru OBAYASHI. "S0510404 Flow field Structure around a NACA0012 airfoil using Synthetic Jets." Proceedings of Mechanical Engineering Congress, Japan 2014 (2014): _S0510404——_S0510404—. http://dx.doi.org/10.1299/jsmemecj.2014._s0510404-.

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INOUE, Yuki, Yasunori NAGATA, Toshinori KOUCHI, and Shinichiro YANASE. "Two Dimensional RANS Analysis of NACA0012 Airfoil at Low Reynolds numbers." Proceedings of Conference of Chugoku-Shikoku Branch 2019.57 (2019): 515. http://dx.doi.org/10.1299/jsmecs.2019.57.515.

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