Relevant bibliographies by topics / NACA airfoil

Contents

  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'NACA airfoil'

Author: Grafiati
Published: 3 June 2025
Last updated: 31 July 2025

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Journal articles on the topic "NACA airfoil"

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Othman, K. A., and A. S. Mahdi Al-Obaidi. "Effect of the wing airfoil shape on the aerodynamics and performance of a jet-trainer aircraft – An optimization approach." Journal of Physics: Conference Series 2120, no. 1 (2021): 012011. http://dx.doi.org/10.1088/1742-6596/2120/1/012011.

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Abstract Among the key factors in developing the performance of military aircraft are its aerodynamic characteristics and performance. This research presents the effect of shape of the wing airfoil on the aerodynamic characteristics and performance of the popular jet trainer aircraft L-39C. The aerodynamic data of different airfoil shapes were used to determine the aerodynamic characteristics and performance of the L-39C for different airfoil shapes in an effort to optimize the aircrafts aerodynamic and performance. NACA 64A012 airfoil is currently used on the L-39C, however, there may exist m
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Zebua, Andrew G., Sheila Tobing, Tajuddin Nur, and Mohammad Akita Indianto. "Numerical Analysis on The Effects of Stagger, Thickness, and Curvature on The Propulsion of Tandem Airfoil." International Journal of Automotive and Mechanical Engineering 20, no. 2 (2023): 10441–56. http://dx.doi.org/10.15282/ijame.20.2.2023.09.0807.

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The study of the aerodynamics of flapping airfoils is crucial to understand the flight of natural flyers and its potential applications in developing micro air vehicles and wind/water turbine blades. There has been much research on the aerodynamics of flapping wings recently, but there is only a little research relating to the tandem airfoil. Therefore, this study is conducted to determine the aerodynamic characteristics of the tandem airfoil at Re = 100000, typical of insect flight. The tandem airfoil is plunging and pitching harmonically. This study numerically analyzes the effects of stagge
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Seralathan, Sivamani, T. Micha Premkumar, S. Thangavel, and G. P. Pradeep. "Numerical Studies on the Effect of Cambered Airfoil Blades on Self-Starting of Vertical Axis Wind Turbine Part 2: NACA 0018 and NACA 63415." Applied Mechanics and Materials 787 (August 2015): 245–49. http://dx.doi.org/10.4028/www.scientific.net/amm.787.245.

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NACA 0012 and NACA 4415 were discussed in Part 1 of the paper to study the capabilities of the airfoil blades by considering the effect of cambered airfoil blade on self-starting of vertical axis wind turbine. The numerical studies are carried out to identify self-starting capability of the airfoil using CFD analysis by studying the flow field over the vertical axis wind turbine blades. In this Part 2 paper, detailed numerical results of asymmetrical NACA 0018 and cambered airfoil NACA 63415 are presented. The lift force generated and the rotor torque induced varies with angle of attack. Based
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Fayyad, Sayel M., Aiman Al Alawin, Suleiman Abu-Ein, et al. "Aerodynamics Analysis Comparison between NACA 4412 and NREL S823 Airfoils." WSEAS TRANSACTIONS ON FLUID MECHANICS 19 (April 2, 2024): 129–41. http://dx.doi.org/10.37394/232013.2024.19.13.

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This paper presents a study of the aerodynamics of a wing or bluff bodies and compares different wing types' behavior against aerodynamic forces. NACA 4412 and NERL S823 airfoils will be analyzed numerically using the ANSYS simulation. The methodology used in this paper depends on collecting data from the last studies, studying the analyzed airfoil models, and constructing an analytical model to show the aerodynamic effects on NACA 4412 and NERL S823 airfoils, and find the total solution. A comparison between NACA 4412 airfoil and NREL'S S823 is presented. It was found that the lift coefficien
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Namrata Deka Baruah, Dimbalita Deka, and Kalyan Kumar Das. "Aerodynamic Analysis of NACA 2412 airfoil using ANSYS." International Research Journal on Advanced Engineering and Management (IRJAEM) 3, no. 02 (2025): 173–77. https://doi.org/10.47392/irjaem.2025.0030.

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Fluid flow analysis over an airfoil is crucial for understanding aerodynamic performance including lift, drag and stability. This work presents a numerical analysis and investigation into the design of airfoils focusing on the NACA 4-digit series. The research employs ANSYS simulation tools to model and analyze the aerodynamics of airfoils. NACA 4-digit airfoil generator is utilized to import the airfoil geometry of NACA 2412 series. A C-shaped computational domain is considered as the fluid domain in which the airfoil geometry is imported. The simulation results provide the variation of press
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Wang, Xiao. "Numerical Study on Aerodynamic Characteristics of Wings of Passenger Aircraft under High Subsonic Conditions." Highlights in Science, Engineering and Technology 93 (May 8, 2024): 56–64. http://dx.doi.org/10.54097/kt89wq35.

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In aerospace engineering, optimizing aerodynamic efficiency under high subsonic flight conditions is paramount. Traditional airfoil research and design methodologies have exhibited limitations, particularly in their efficacy at speeds approaching high subsonic speed, where drag reduction and lift enhancement become critical for performance optimization. These conventional approaches often fall short of addressing the nuanced aerodynamic challenges presented by high subsonic regimes. Addressing these limitations, the present research adopts a computational fluid dynamics (CFD) approach, utilizi
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Raj Mohamed, Mohamed Arif, Rajesh Yadav, and Ugur Guven. "Flow separation control using a bio-inspired nose for NACA 4 and 6 series airfoils." Aircraft Engineering and Aerospace Technology 93, no. 2 (2021): 251–66. http://dx.doi.org/10.1108/aeat-08-2019-0170.

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Purpose This paper aims to achieve an optimum flow separation control over the airfoil using a passive flow control method by introducing a bio-inspired nose near the leading edge of the National Advisory Committee for Aeronautics (NACA) 4 and 6 series airfoil. In addition, to find the optimised leading edge nose design for NACA 4 and 6 series airfoils for flow separation control. Design/methodology/approach Different bio-inspired noses that are inspired by the cetacean species have been analysed for different NACA 4 and 6 series airfoils. Bio-inspired nose with different nose length, nose dep
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Singh, Abhineet, Sonali Mitra, S. V. H. Nagendra, and Pragyan Jain. "Selection of Airfoils for Vertical Axis Wind Turbines for Low Speed, Low Altitude Regions of Central India." International Journal of Advanced Research in Computer Science and Software Engineering 7, no. 11 (2017): 113. http://dx.doi.org/10.23956/ijarcsse.v7i11.450.

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The present paper deals with the selection of airfoil profile for VAWTs which is to be installed in the college campus, located in Central India region. Both experimental and numerical analysis he been carried out for the three selected airfoils, NACA 0012, NACA 0015 & S2027. The results show a good correlation with the existing literature. Airfoil profile S2027 has been chosen which best suits our condition.
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Tanabi, Naser, Agesinaldo Matos Silva, Marcosiris Amorim Oliveira Pessoa, and Marcos Sales Guerra Tsuzuki. "Robust Algorithm Software for NACA 4-Digit Airfoil Shape Optimization Using the Adjoint Method." Applied Sciences 13, no. 7 (2023): 4269. http://dx.doi.org/10.3390/app13074269.

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Optimizing the aerodynamic shape of an airfoil is a critical concern in the aviation industry. The introduction of flexible airfoils has allowed the shape of the airfoil to vary, depending on the flight conditions. Therefore, in this study, we propose an algorithm that is capable of robustly optimizing the shape of the airfoil based on variable parameters of the airfoil and flight conditions. The proposed algorithm can be understood as an optimization method, which employs the adjoint method, a powerful tool for estimating the sensitivity of the model output to the input in numerous studies. F
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Kriswanto, Kriswanto, Mohammad Misbachul Munir, Dony Hidayat Al-Janan, et al. "Simulation of Torque, Tip Speed Ratio, Power, and Power Coefficient of 1 MW Horizontal Axis Wind Turbine in Modified NACA 4412-2412 Variation of Airfoil Blades." Journal of Advanced Research in Fluid Mechanics and Thermal Sciences 120, no. 2 (2024): 155–73. http://dx.doi.org/10.37934/arfmts.120.2.155173.

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The rotor power of HAWT can be affected by the type of airfoil and airfoil modifications on a blade. However, no study of wind turbine blades from arranges types of airfoils or altering the leading and trailing edges has been conducted. To determine the maximum torque, TSR, power, and power coefficient values at Horizontal Axis Wind Turbine (HAWT) 1MW, simulations of turbine blades with various airfoil designs are performed. NACA 4412 and 2412 airfoils were utilized, with the leading and trailing edges modified. The method used is Blade Element Momentum simulation on 20 blade variations with m
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Dissertations / Theses on the topic "NACA airfoil"

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Giles, David Michael. "Aerodynamic Performance Enhancement of a NACA 66-206 Airfoil Using Supersonic Channel Airfoil Design." DigitalCommons@CalPoly, 2009. https://digitalcommons.calpoly.edu/theses/186.

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Supersonic channel airfoil design techniques have been shown to significantly reduce drag in high-speed flows over diamond shaped airfoils by Ruffin and colleagues. The effect of applying these techniques to a NACA 66-206 airfoil is presented. The design domain entails channel heights of 8-16.6% thickness-to-chord and speeds from Mach 1.5-3.0. Numerical simulations show an increase in the lift-to-drag ratio for airfoils at Mach 2.5 at a 35,000-ft altitude with a 12% channel height geometry showing a benefit of 17.2% at 6-deg angle of attack and a sharp channel leading edge. Wave drag is signif
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Altmann, Gregory F. "An Investigative Study of Gurney Flaps on a NACA 0036 Airfoil." DigitalCommons@CalPoly, 2011. https://digitalcommons.calpoly.edu/theses/524.

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This project examined the effect of Gurney flaps on a 2D, 2-ft chord NACA 0036 airfoil in the Cal Poly 3’x4’ low speed wind tunnel at 25 m/s. It also covered the numerical simulation of the experiment in computational fluid dynamics (CFD). During the study, problems with the wind tunnel data were seen. After a careful diagnosis, the problem was traced to dirty flow conditioners which were subsequently replaced. Five Gurney flaps at 1, 2, 3, 4, and 5% of the chord were tested. The Gurney flaps had the effect of eliminating the lift reversal effect and lowering the profile drag at low angles
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Islam, Md Monirul. "Nonlinear normal force indicial responses for a 2-D NACA 0015 airfoil." Ohio : Ohio University, 1991. http://www.ohiolink.edu/etd/view.cgi?ohiou1183730957.

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Digavalli, Sasi K. (Sasi Kumar). "Dynamic stall of a NACA 0012 airfoil in laminar flow." Thesis, Massachusetts Institute of Technology, 1993. http://hdl.handle.net/1721.1/12206.

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Castañeda, Vergara David Armando. "Active Control of Flow over an Oscillating NACA 0012 Airfoil." The Ohio State University, 2020. http://rave.ohiolink.edu/etdc/view?acc_num=osu1587420875168203.

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Fang, Kuan-Chieh. "Nonlinear aerodynamic responses in tow tank study for a two dimensional NACA 0015 airfoil." Ohio : Ohio University, 1992. http://www.ohiolink.edu/etd/view.cgi?ohiou1172265691.

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Katam, Vamsidhar. "SIMULATION OF LOW-RE FLOW OVER A MODIFIED NACA 4415 AIRFOIL WITH OSCILLATING CAMBER." UKnowledge, 2005. http://uknowledge.uky.edu/gradschool_theses/339.

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Recent interest in Micro Aerial Vehicles (MAVs) and Unmanned Aerial Vehicles (UAVs) have revived research on the performance of airfoils at relatively low Reynolds numbers. A common problem with low Reynolds number flow is that separation is almost inevitable without the application of some means of flow control, but understanding the nature of the separated flow is critical to designing an optimal flow control system. The current research presents results from a joint effort coupling numerical simulation and wind tunnel testing to investigate this flow regime. The primary airfoil for these st
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Li, Sihao. "Effect of aeroelasticity in tow tank strain gauge measurements on a NACA 0015 airfoil." Ohio : Ohio University, 1993. http://www.ohiolink.edu/etd/view.cgi?ohiou1175713922.

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Nowak, Lisa M. "Computational investigations of a NACA 0012 airfoil in low Reynolds number flows." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1992. http://edocs.nps.edu/npspubs/scholarly/theses/1992/Sep/92Sep_Nowak.pdf.

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Thesis (Degree in Aeronautical and Astronautical Engineer)--Naval Postgraduate School, Sept. 1992.<br>Thesis advisor(s): M.F. Platzer and M. Chandrasekhara. "September 1992." Includes bibliographical references. Also available online.
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Loretz, Yves Daniel. "Flow control on a NACA 4418 airfoil using streamwise synthetic jet actuators." Thesis, Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/16377.

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Books on the topic "NACA airfoil"

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J, Camba, Morris P. M, and United States. National Aeronautics and Space Administration, eds. Aerodynamic data banks for Clark-Y, NACA 4-digit, and NACA 16-series airfoil families. National Aeronautics and Space Administration, Lewis Research Center, 1986.

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Corrigan, Robert D. Performance comparison between NACA 23024 and NACA 64-́618 airfoil configured rotors for horizontal-axis wind turbines. National Aeronautics and Space Administration, 1985.

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Corrigan, Robert D. Performance comparison between NACA 23024 and NACA 64-618 airfoil configured rotors for horizontal-axis wind turbines. National Aeronautics and Space Administration, 1985.

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Robert, Shaw, Newton James E, and United States. National Aeronautics and Space Administration., eds. Ice shapes and the resulting drag increase for a NACA 0012 airfoil. National Aeronautics and Space Administration, 1985.

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McCroskey, W. J. A critical assessment of wind tunnel results for the NACA 0012 airfoil. National Aeronautics and Space Administration, Ames Research Center, 1987.

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Mineck, Raymond E. Effect of full-chord porosity on aerodynamic characteristics of the NACA 0012 airfoil. Langley Research Center, 1996.

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H, Bond Thomas, and United States. National Aeronautics and Space Administration., eds. Experimental and computational ice shapes and resulting drag increase for a NACA 0012 airfoil. National Aeronautics and Space Administration, 1992.

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M, Gregorek G., and United States. National Aeronautics and Space Administration., eds. Wind tunnel evaluation of a truncated NACA 64-621 airfoil for wind turbine applications. National Aeronautics and Space Administration, 1987.

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H, Bond Thomas, and United States. National Aeronautics and Space Administration., eds. Experimental and computational ice shapes and resulting drag increase for a NACA 0012 airfoil. National Aeronautics and Space Administration, 1992.

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Poinsatte, Philip E. Heat transfer measurements from a NACA 0012 airfoil in flight and in the NASA Icing Research Tunnel. Lewis Research Center, 1990.

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Book chapters on the topic "NACA airfoil"

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Secretan, Yves, Gouri Dhatt, and Dinh Nguyen. "Compressible Viscous Flow Around a NACA-0012 Airfoil." In Numerical Simulation of Compressible Navier-Stokes Flows. Vieweg+Teubner Verlag, 1987. http://dx.doi.org/10.1007/978-3-322-87873-1_13.

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Livya, E., R. Sai Anirudh, V. Vignesh, B. Prasannavenkatesh, and S. Nadaraja Pillai. "Experimental Analysis of Implementing Roughness on NACA 0018 Airfoil." In Lecture Notes in Mechanical Engineering. Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-13-2697-4_10.

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Jalasabri, Jafirdaus, Mohamed Sukri Mat Ali, Fairuz Izzuddin Romli, and Nurshafinaz Mohd Maruai. "Noise Estimation of NACA 0012 Airfoil Using DES Method." In Lecture Notes in Mechanical Engineering. Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-99-6874-9_7.

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Nitya, MV, and Rajesh Ranjan. "Numerical investigation of transitional flows over NACA 0012 Airfoil." In Lecture Notes in Mechanical Engineering. Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-6270-7_64.

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AlMutairi, J., I. AlQadi, and E. ElJack. "Large Eddy Simulation of a NACA-0012 Airfoil Near Stall." In Direct and Large-Eddy Simulation IX. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-14448-1_49.

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Solanki, Aditya, Shashank Jibhakate, Vivek Mahadule, Yash Belekar, and Prasad Hatwalne. "Comparative analysis of NACA 0015 airfoil with bump using CFD." In Recent Advances in Material, Manufacturing, and Machine Learning. CRC Press, 2024. http://dx.doi.org/10.1201/9781003450252-32.

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Varda, Kenan, Ernad Bešlagić, and Nermina Zaimović-Uzunović. "Measurement of NACA Airfoil Characteristic Parameters on 3D Printed Models." In New Technologies, Development and Application IV. Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-75275-0_36.

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Tenaud, C., and Ta Phuoc Loc. "Numerical Simulation of Unsteady Compressible Viscous Flow around NACA 0012 Airfoil." In Numerical methods for the Navier-Stokes equations. Vieweg+Teubner Verlag, 1994. http://dx.doi.org/10.1007/978-3-663-14007-8_28.

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Mukesh, Ishwar, Aakash Kaushik, Naushad Ahmad Ansari, and M. Zunaid. "Study of Effect of Leading-Edge Tubercles on NACA 4412 Airfoil." In Lecture Notes in Mechanical Engineering. Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-16-9523-0_21.

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Tebbiche, Hocine, and Mohammed S. Boutoudj. "Passive Control on the NACA 4412 Airfoil and Effects on the Lift." In Design and Modeling of Mechanical Systems - II. Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-17527-0_77.

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Conference papers on the topic "NACA airfoil"

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Li, Yuchen, Mingjian Yang, Yining Zhang, Wen Tian, and Lei Yang. "NACA-0006 Aerodynamic Characterization of Airfoil High-Speed Flow Field." In 2024 12th International Conference on Traffic and Logistic Engineering (ICTLE). IEEE, 2024. http://dx.doi.org/10.1109/ictle62418.2024.10703880.

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Li, Yuchen, Mingjian Yang, Wen Tian, and Yining Zhang. "NACA-0006 Aerodynamic Characterization of Airfoil High-Speed Flow Field." In 2024 AIAA DATC/IEEE 43rd Digital Avionics Systems Conference (DASC). IEEE, 2024. http://dx.doi.org/10.1109/dasc62030.2024.10749356.

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Heletkanycz, Andrew, Christopher Thurman, and James Coder. "Airfoil Parameterization using an Improved Class-Shape Transformation and Chebyshev Polynomials." In Vertical Flight Society 81st Annual Forum and Technology Display. The Vertical Flight Society, 2025. https://doi.org/10.4050/f-0081-2025-92.

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A method for the parameterization of an arbitrary airfoil using a transformation and Chebyshev polynomial interpolation is investigated. The airfoil was transformed into a continuous function using the Class Shape Transformation. A square root spacing was used to smooth out the slope discontinuity found at the origin. This mapping reduces oscillations in the polynomial interpolation caused by the slope discontinuity at the origin. Interpolating a range of NACA 4-digit series airfoils showed that these airfoils could be accurately represented with as little as 10 polynomial terms. However, prob
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Hodara, Joachim, Andrew Lind, Marilyn Smith, and Anya Jones. "Collaborative Investigation of the Aerodynamic Behavior of Airfoils in Reverse Flow." In Vertical Flight Society 71st Annual Forum & Technology Display. The Vertical Flight Society, 2015. http://dx.doi.org/10.4050/f-0071-2015-10099.

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Two fundamental models of the flow (static and dynamic) over airfoils in the reverse flow region of a helicopter in forward flight are investigated experimentally and computationally at Reynolds numbers of O(10⁵). The first model examines the time-averaged and unsteady flow resulting from a two-dimensional NACA 0012 airfoil held at a static angle of attack. Computational tools successfully predict the presence of three unsteady wake regimes and time-averaged airloads measured experimentally at the University of Maryland (UMD). A second model is investigated by pitching a NACA 0012 airfoil thro
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Modarres, Ramin, David Peters, and Jacob Gaskill. "Dynamic Stall with Circulation Pulse and Hysteresis for NACA 0012 and VR-12 Airfoils." In Vertical Flight Society 71st Annual Forum & Technology Display. The Vertical Flight Society, 2015. http://dx.doi.org/10.4050/f-0071-2015-10093.

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Airfoils undergoing dynamic stall often display a secondary lift peak after the lift has begun to decrease. A study of this phenomenon for the NACA 0012 and VR-12 airfoils shows that the secondary peak is followed by a damped oscillation in lift. It is found that this under-damped lift can be modeled by an ONERA type equation for secondary lift that is driven by a simple pulse. It is speculated that the physical basis of this pulse is the attaching of a secondary vortex to the airfoil. The onset and duration of this pulse can be predicted in terms of angle of attack in a general time-domain si
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Sharma, Saurabh, and Shibu Clement. "CFD Simulation of the Flow Characteristics of NACA 0012, NACA 6409, and DHMTU Airfoils in Ground Effect." In ASME 2014 4th Joint US-European Fluids Engineering Division Summer Meeting collocated with the ASME 2014 12th International Conference on Nanochannels, Microchannels, and Minichannels. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/fedsm2014-21131.

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Ground effect is a phenomenon caused by the presence of a fixed boundary layer below a wing. This results in an effective increase in lift to drag ratio of the airfoil. The available literature on this phenomenon is very limited; also the types of airfoils used in traditional aircrafts are not suited for ground effect vehicles, so a computational study has been done comparing traditional airfoils (NACA series) with ground effect airfoil (DHMTU). In this paper, the aerodynamic characteristics of a NACA 6409, NACA 0012, DHMTU 12-35.3-10.2-80.12.2[1] section in ground effect were numerically stud
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Kamenická, Daniela, and Martin Bugaj. "Aerodynamic airfoils and their applications." In Práce a štúdie. University of Žilina, 2021. http://dx.doi.org/10.26552/pas.z.2021.1.10.

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This work focuses on aerodynamic airfoils and their application. The significant aim of this work is to introduce and analyse different types of airfoils and their importance. The first part of the paper examines aerodynamic characteristics, airfoil geometry and brings the historical evolution of certain types of airfoils. The second part of the paper considers different databases, and closely examines the NACA database and its numerical labelling by looking at digit series label, which follows the acronym NACA, indicating the airfoil's shape. The main body of the paperillustrates the real-lif
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Oztekin, Ezgi S., and James T. Riley. "Ice accretion on a NACA 23012 airfoil." In 9th AIAA Atmospheric and Space Environments Conference. American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-3760.

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Das, Biranchi Narayana, Manoj Ukamanal, and Atal Bihari Harichandan. "Adjoint Based Optimization of NACA 4412 Airfoil." In 2022 International Interdisciplinary Conference on Mathematics, Engineering and Science (MESIICON). IEEE, 2022. http://dx.doi.org/10.1109/mesiicon55227.2022.10093324.

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Oztekin, Ezgi S., and James T. Riley. "Ice accretion on a NACA 23012 airfoil." In 2018 Atmospheric and Space Environments Conference. American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-2860.

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Reports on the topic "NACA airfoil"

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Chaudhary, R. I., and D. T. Williamson. Endplate Effectiveness for a NACA 0015 Airfoil. Defense Technical Information Center, 1992. http://dx.doi.org/10.21236/ada373750.

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Covert, Eugene E., Michael J. Fletcher, Kirk J. Flittie, and Samuel W. Linton. On the Unsteady Characteristics of Flows Around an NACA 0012 Airfoil. Defense Technical Information Center, 1986. http://dx.doi.org/10.21236/ada179654.

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Ostowari, C., and D. Naik. Post-stall wind tunnel data for NACA 44XX series airfoil sections. Office of Scientific and Technical Information (OSTI), 1985. http://dx.doi.org/10.2172/5791328.

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Reuss, R. L., M. J. Hoffman, and G. M. Gregorek. Effects of Surface Roughness and Vortex Generators on the NACA 4415 Airfoil. Office of Scientific and Technical Information (OSTI), 1995. http://dx.doi.org/10.2172/206541.

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Hoffmann, M. J., R. Reuss Ramsay, and G. M. Gregorek. Effects of grit roughness and pitch oscillations on the NACA 4415 airfoil. Office of Scientific and Technical Information (OSTI), 1996. http://dx.doi.org/10.2172/266691.

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6

Law, S., and G. Gregorek. Wind tunnel evaluation of a truncated NACA 64-621 airfoil for wind turbine applications. Office of Scientific and Technical Information (OSTI), 1987. http://dx.doi.org/10.2172/6443460.

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Bigdeli, Mohammad, та Vahid Monfared. Investigation and Comparison of Stall Angle of Airfoil NACA 0012 in Reynolds Number of 3 × 106 with K‑ω SST, Realizable k‑ε, Spalart-Allmaras Turbulence Models. "Prof. Marin Drinov" Publishing House of Bulgarian Academy of Sciences, 2020. http://dx.doi.org/10.7546/crabs.2020.03.13.

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