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Dissertations / Theses on the topic 'NACA airfoil'

Author: Grafiati

Published: 3 June 2025

Last updated: 31 July 2025

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1

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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2

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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3

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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4

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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5

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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6

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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7

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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8

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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9

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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10

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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11

Tober, Hampus, and Erik Hänninger. "Evaluation of OpenFOAM performance for RANS simulationsof flow around a NACA 4412 airfoil." Thesis, KTH, Skolan för teknikvetenskap (SCI), 2018. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-231098.

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The purpose of this study is to evaluate how well the RANS models implemented in the open-source software OpenFOAM performs when simulating flow around a NACA 4412 airfoil with a turbulent boundary layer. After assessing the different models and performing several tests, the Spalart Allmaras model was chosen to be the best candidate for this airfoil. The model was validated against several different references, including a flying-hot-wire study by Coles and Wadcock [5] for a chord based Reynolds number of 1.500.000, and a Direct Numerical Simulation (DNS) performed by Vinuesa et al. [18] at th

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12

Sullivan, Taylor D. "REDUCED ORDER MODELING OF FLOW OVER A NACA 0015 AIRFOIL FOR FUTURE CONTROL APPLICATION." Miami University / OhioLINK, 2014. http://rave.ohiolink.edu/etdc/view?acc_num=miami1407295741.

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13

Stolt, Adam James. "Experimental Evaluation of a NACA 0021 Airfoil Employing Shape-Memory Alloy for Active Flow Control." Thesis, North Dakota State University, 2018. https://hdl.handle.net/10365/28715.

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Current aircraft use actuators to alter the wing geometry and generate the ideal flight characteristics which is known to be a method of active flow control. By replacing the heavy electric and hydraulic actuators currently used in aircraft wings with lighter and smaller shape memory alloys (SMAs), the mass of an aircraft can be reduced. Therefore, research was conducted to design and build an airfoil using SMAs as the actuator for improving the airfoil?s aerodynamic performance. The SMA actuated airfoil was evaluated using advanced flow diagnostic methods and was found to operate with a highe

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14

Scarbrough, William T. "NACA four-digit airfoil section generation using cubic parametric curve segments and the golden section /." Online version of thesis, 1992. http://hdl.handle.net/1850/11033.

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15

Jensen, Christopher Douglas. "Global Pressure and Temperature Surface Measurements on a NACA 0012 Airfoil in Oscillatory Compressible Flow at Low Reduced Frequencies." The Ohio State University, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=osu1331075431.

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16

Siauw, Wei Long. "Transient process of separation and attachment over a NACA 0015 airfoil controlled by fluidic vortex generators." Poitiers, 2008. http://www.theses.fr/2008POIT2313.

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Ce travail expérimental est consacré à l’étude du décollement et du recollement transitoire sur profil NACA 0015 contrôlé par des Générateurs de Vortex Fluidique (FVG). Des essais sont effectués à un nombre de Reynolds de 1 million, et à une incidence de 11o. L’écoulement sans contrôle est caractérisé par une zone décollée qui commence à xA-c=0,7 à partir du bord d'attaque (soit 30% de la corde) avec un minimum de vibrations. Pour effectuer le contrôle de l’écoulement, 44 FVG sont installés à xA-c=0,3. Les effets de la FVG sont caractérisés par une augmentation de 16% du coefficient de portanc

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17

Sahoo, Dipankar. "Experimental analysis of the vorticity and turbulent flow dynamics of a pitching airfoil at realistic flight (helicopter) conditions." Diss., Texas A&M University, 2008. http://hdl.handle.net/1969.1/85893.

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Improved basic understanding, predictability, and controllability of vortex-dominated and unsteady aerodynamic flows are important in enhancement of the performance of next generation helicopters. The primary objective of this research project was improved understanding of the fundamental vorticity and turbulent flow physics for a dynamically stalling airfoil at realistic helicopter flight conditions. An experimental program was performed on a large-scale (C = 0.45 m) dynamically pitching NACA 0012 wing operating in the Texas A&M University large-scale wind tunnel. High-resolution particle ima

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18

Lundberg, Marcus. "Aerodynamics of Insect Flight : Effects of wind gusts on a rigid flapping NACA 0012 airfoil at Re = 3000." Thesis, KTH, Mekanik, 2015. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-167123.

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Insects and small flyers operate at Reynolds numbers ranging from approximately 10-105 , where viscous forces are important. Due to their small size and weight, they are sensitive to small changes in the free stream during flight, such as wind gusts. First, the aerodynamics of flapping flight is briey explained. Then the lift, drag and power usage for a flapping NACA 0012 airfoil is simulated in ANSYS Fluent for different oncoming wind directions. The aim of the report is to understand how the pitching amplitude, the apping frequency and the plunging amplitude can be adjusted to compensate for

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19

Mish, Patrick F. "Mean Loading and Turbulence Scale Effects on the Surface Pressure Fluctuations Occurring on a NACA 0015 Airfoil Immersed in Grid Generated Turbulence." Thesis, Virginia Tech, 2001. http://hdl.handle.net/10919/33751.

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Detailed surface pressure measurements have been made on a NACA 0015 immersed in two grid generated homogenous flows at Re = 1.17 x 10^6 for a = 0Â°, 4Â°, 8Â°, 12Â°, 16Â°, and 20Â°. The goal of this measurement was to reveal and highlight mean loading and turbulence scale effects on surface pressure fluctuations resulting from turbulence/airfoil interaction. Also, measurements are compared with the theory of Amiet (1976a,b). The surface pressure response shows a dependance on angle of attack, the nature of which is related to the relative chord/turbulence scale. The dependance on turbulenc

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20

Rueger, Mathew Lee. "An experimental investigation of the effect of vortex generators on the aerodynamic characteristics of a NACA 0021 airfoil undergoing large amplitude pitch oscillations." The Ohio State University, 1988. http://rave.ohiolink.edu/etdc/view?acc_num=osu1407506629.

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21

Van, Dyken Robert D. "Experimental and computational analysis of separation bubble behavior for compressible, steady and oscillatory flows over a NACA 0012 airfoil at M=0.3 and a reynolds number of 540,000." Thesis, Monterey, California. Naval Postgraduate School, 1997. http://hdl.handle.net/10945/8365.

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Approved for public release; distribution is unlimited<br>In this thesis, the separation bubble behavior and its effect on the steady and dynamic stall characteristics of a thin airfoil in a compressible flow at a transitional Reynolds number was studied. For such flows, laminar separation occurs near the airfoil leading edge, but turbulent reattachment occurs within a short distance downstream, forming a separation bubble in the underlying region. Two experimental techniques, point diffraction interferometry (PDI) and laser doppler velocimetry (LDV), were used to acquire detailed flowfield in

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22

Loo, Felipe Manuel. "Numerical Study of Limit Cycle Oscillation Using Conventional and Supercritical Airfoils." Scholarly Repository, 2008. http://scholarlyrepository.miami.edu/oa_theses/176.

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Limit Cycle Oscillation is a type of aircraft wing structural vibration caused by the non-linearity of the system. The objective of this thesis is to provide a numerical study of this aeroelastic behavior. A CFD solver is used to simulate airfoils displaying such an aeroelastic behavior under certain airflow conditions. Two types of airfoils are used for this numerical study, including the NACA64a010 airfoil, and the supercritical NLR 7301 airfoil. The CFD simulation of limit cycle oscillation (LCO) can be obtained by using published flow and structural parameters. Final results from the CFD s

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23

Rajesh, Ravi. "Numerical Investigation of NACA Airfoil and Wind Turbine Airfoil." Thesis, 2018. http://ethesis.nitrkl.ac.in/9848/1/2018_MT_216CE4077_RRajesh_Numerical.pdf.

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Assessment of drag coefficient frequently requires experiment in wind tunnel and experimenting with wind tunnel is limited to certain size model. However, Computational Fluid Dynamics (CFD) provides an alternate method to perform an aerodynamic analysis and is playing a vital role as a design tool in many industries like aerospace, automotive, etc. The main objective of this research is to investigate flow pattern and to study the aerodynamic analysis of NACA airfoils and NREL airfoils. In this study, NACA ooo6, NACA oo12, and NACA 1412 airfoils were considered as NACA airfoils, whereas S819,

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24

Pruski, Brandon. "Leading Edge Flow Structure of a Dynamically Pitching NACA 0012 Airfoil." Thesis, 2012. http://hdl.handle.net/1969.1/148372.

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The leading edge flow structure of the NACA 0012 airfoil is experimentally investigated under dynamic stall conditions (M = 0.1; α = 16.7◦, 22.4◦; Rec = 1× 10^6) using planar particle image velocimetry. The airfoil was dynamically pitched about the 1/4 chord at a reduced frequency, k = 0.1. As expected, on the upstroke the flow remains attached in the leading edge region above the static stall angle, whereas during downstroke, the flow remains separated below the static stall angle. A phase averaging procedure involving triple velocity decomposition in combination with the Hilbert transform en

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25

Moreira, Diego Carlos Rua. "Passive Control on Transonic Flow Study of Cavity Effect on NACA 4412 Airfoil." Master's thesis, 2018. https://repositorio-aberto.up.pt/handle/10216/115983.

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26

Moreira, Diego Carlos Rua. "Passive Control on Transonic Flow Study of Cavity Effect on NACA 4412 Airfoil." Dissertação, 2018. https://repositorio-aberto.up.pt/handle/10216/115983.

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27

Boutilier, Michael Stephen Hatcher. "Experimental Investigation of Transition over a NACA 0018 Airfoil at a Low Reynolds Number." Thesis, 2011. http://hdl.handle.net/10012/6044.

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Shear layer development over a NACA 0018 airfoil at a chord Reynolds number of 100,000 was investigated experimentally. The effects of experimental setup and analysis tools on the results were also examined. The sensitivity of linear stability predictions for measured separated shear layer velocity profiles to both the analysis approach and experimental data scatter was evaluated. Analysis approaches that are relatively insensitive to experimental data scatter were identified. Stability predictions were shown to be more sensitive to the analysis approach than to experimental data scatter, wit

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28

Subroto, Phutut Hadi. "Viscous/inviscid interaction analysis of the aerodynamic performance of the NACA 65-213 airfoil." Thesis, 1987. http://hdl.handle.net/10945/22579.

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29

Liang, Pan Jiann, and 潘建良. "The Investigations of Vortical Structure for NACA Series Airfoil by the Effect of S.H.M." Thesis, 2004. http://ndltd.ncl.edu.tw/handle/07765088366866706446.

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碩士<br>國立中興大學<br>機械工程學系<br>92<br>In this study, an experimental method was used to visualize the flow structure and vortex breakdown at the upper of NACA series airfoils for the different model type and angle of attack with large amplitude pitching motion. This experiment was proceeded by the open-type wind tunnel, the model type were NACA0012, NACA0015, NACA0018 airfoil, the pitching motion center was at 1/4 chord length and pitching amplitude were ±50, ±100, and ±150. The free stream velocity is 2 m/sec, Reynolds number is 1.5×104, and the frequency of pitching is 0.5Hz. In this st

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30

Hung, Wei-Chia, and 洪偉家. "The Effects of Surface Roughness on the Characteristics of Surface Pressure of NACA 0015 Airfoil." Thesis, 2005. http://ndltd.ncl.edu.tw/handle/68260099098319045875.

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碩士<br>國立中興大學<br>機械工程學系<br>93<br>The present study was intended to investigate the surface pressure of NACA 0015 airfoil at upper and lower surface due to the sandblast roughness. The experiment was proceeded in an low-speed and open-type wind tunnel. The dynamic behavior of surface pressure of NACA 0015 airfoil was analyzed at various angle of attack, Reynolds number, number of sandblast, and width of sandblast. The freestream velocity was operated at 5~20 m/s and the corresponding Reynolds number at 3.8×104~1.5×105 which based on the chord of the wing. The purpose of this study was intended t

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31

Bernardo, André Rodrigues. "Estudo das características aerodinâmicas de perfis alares." Master's thesis, 2017. http://hdl.handle.net/10316/83064.

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Dissertação de Mestrado Integrado em Engenharia Mecânica apresentada à Faculdade de Ciências e Tecnologia<br>Esta dissertação de mestrado tem como objectivo estudar as forças que actuam sobre asas com diferentes alongamentos, quando sujeitas a um escoamento subsónico. As asas estudadas têm um perfil simétrico NACA 0012. Este estudo foi realizado no Laboratório de Mecânica dos Fluidos do Departamento de Engenharia Mecânica.Foi estudada a variação da intensidade e direcção das forças e momentos aplicados na asa, e dos respectivos coeficientes aerodinâmicos, com a variação do ângulo de ataque, do

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