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Dissertations / Theses on the topic 'NACA0012'

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

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1

Leroux, Romain. "Inférence bayésienne pour la reconstruction d'écoulements complexes - Application au profil NACA0012." Phd thesis, Université de Poitiers, 2012. http://tel.archives-ouvertes.fr/tel-00766239.

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Cette thèse se place dans le cadre de la calibration de modèles réduits d'écoulement à partir de séquences expérimentales acquises par PIV résolue en temps autour d'un profil NACA0012 à différents angles d'incidence et nombres de Reynolds. Un modéle à espace d'état régissant l'évolution des variables d'état du modèle réduit POD-Galerkin et mesurant de manière directe ou indirecte une partie ou l'ensemble de ces variables d'état est alors utilisé. Une première partie est consacrée à l'application d'estimateurs bayésiens issus de l'assimilation séquentielle de données sur le modèle réduit POD-Ga
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2

Huang, Liang. "OPTIMIZATION OF BLOWING AND SUCTION CONTROL ON NACA0012 AIRFOIL USING GENETIC ALGORITHM WITH DIVERSITY CONTROL." UKnowledge, 2004. http://uknowledge.uky.edu/gradschool_diss/385.

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Active control of the flow over an airfoil is an area of heightened interest in the aerospace community. Previous research on flow control design processes heavily depended on trial and error and the designers knowledge and intuition. Such an approach cannot always meet the growing demands of higher design quality in less time. Successful application of computational fluid dynamics (CFD) to this kind of control problem critically depends on an efficient searching algorithm for design optimization. CFD in conjunction with Genetic Algorithms (GA) potentially offers an efficient and robust optimi
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3

Kasibhotla, Venkata ravishankar. "3D Dynamic Stall Simulation of Flow over NACA0012 Airfoil at 10⁵ and 10⁶ Reynolds Numbers." Thesis, Virginia Tech, 2014. http://hdl.handle.net/10919/56662.

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The work presented in this thesis attempts to provide an understanding of the physics behind the dynamic stall process by simulating the flow past pitching NACA-0012 airfoil at 100,000 and 1 million Reynolds number based on the chord length of the airfoil and at different reduced frequencies of 0.188 and 0.25 respectively in a three dimensional flow field. The mean angles of attack are 12 deg. and 15 deg. and the amplitudes of pitching are 6 deg. and 10 deg. respectively. The turbulence in the flow field is resolved using large eddy simulations with dynamic Smagorinsky model at the sub grid sc
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4

Huang, Liang. "Optimization of blowing and suction control on NACA0012 airfoil using genetic algoirthm with diversity control." Lexington, Ky. : [University of Kentucky Libraries], 2004. http://lib.uky.edu/ETD/ukymeen2004d00153/LiangDis.pdf.

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Thesis (M.S.)--University of Kentucky, 2004.<br>Title from document title page (viewed Oct. 12, 2004). Document formatted into pages; contains xii, 113 p. : ill. Includes abstract and vita. Includes bibliographical references (p. 102-112).
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5

Bueno, Ana Paula Franco. "Análise experimental das medidas de pressão em regime não-estacionário em um perfil de aerofólio NACA0012." Universidade de São Paulo, 2007. http://www.teses.usp.br/teses/disponiveis/18/18148/tde-03022016-092628/.

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As estruturas aeronáuticas estão sujeitas a diversas solicitações, devido principalmente às interações com o escoamento aerodinâmico, que podem causar distúrbios e vibrações, comprometendo seu desempenho. As medidas aerodinâmicas aplicadas em uma aeronave podem ser obtidas por simulações computacionais ou testes experimentais. No entanto, podem existir imperfeições na simulação computacional, como por exemplo, se conseguir reproduzir algumas condições de vôo real. Sendo assim, diversas pesquisas vêm sendo realizadas para solucionar estes problemas. Dentre elas estão os testes experimentais fei
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6

Norrby, David, and Thomas Långfors. "ANALYS AV NACA0018 VINGPPROFIL." Thesis, KTH, Mekanik, 2011. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-103473.

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7

Debien, Antoine. "Étude électromécanique et optimisation d'actionneurs plasmas à décharge à barrièrediélectrique – Application au contrôle de décollement sur un profil d'aile de type NACA0015." Thesis, Poitiers, 2013. http://www.theses.fr/2013POIT2253/document.

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Cette thèse est effectuée dans le cadre du projet Européen "PlasmAero" dont le but est de développer et d'étudier des actionneurs plasmas, et de démontrer leur capacité à contrôler des écoulements aérodynamiques. L'actionneur plasma à Décharge à Barrière Diélectrique (DBD) de surface est un moyen innovant pour contrôler un écoulement en utilisant le vent électrique induit par la force électrohydrodynamique (EHD) générée au sein du gaz ionisé. Une première partie est dédiée à l'étude des actionneurs plasmas. L'influence de la géométrie de l'électrode active d'une DBD est précisée par des mesure
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8

Labroquère, Jérémie. "Optimisation de dispositifs de contrôle actif pour des écoulements turbulents décollés." Thesis, Nice, 2014. http://www.theses.fr/2014NICE4096/document.

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Les stratégies de contrôle d’écoulement, telles que le soufflage / aspiration, ont prouvé leur efficacité à modifier les caractéristiques d’écoulement à des fins diverses en cas de configurations usuellement simples. Pour étendre cette approche sur des cas industriels, la simulation de dispositifs à échelle réelle et l’optimisation des paramètres de contrôle s’avèrent nécessaires. L’objectif de cette thèse est de mettre en place une procédure d’optimisation pour résoudre cette catégorie de problèmes. Dans cette perspective, l’organisation de la thèse est divisé en trois
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9

Audier, Pierre. "Etude d'une décharge à barrière diélectrique surfacique. Application au contrôle d'écoulement autour d'un profil d'aile de type NACA 0012." Phd thesis, Université d'Orléans, 2012. http://tel.archives-ouvertes.fr/tel-00843633.

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Dans un contexte de croissance du trafic aérien et dans le but de réduire la consommation de carburant ainsi que les émissions de polluants dans l'atmosphère, l'avion de demain se doit d'être plus respectueux de l'environnement. Dans un objectif d'optimisation de ses performances aérodynamiques,d'importantes activités de recherche sont menées dans le monde pour étudier de nouveaux dispositifs de contrôle actif des écoulements en temps réel. Depuis une dizaine d'années, l'utilisation de la décharge à barrière diélectrique surfacique comme actionneur plasma pour le contrôle d'écoulements suscite
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10

Camacho, Emanuel António Rodrigues. "Numerical Analysis of a Plunging NACA0012 Airfoil." Master's thesis, 2019. http://hdl.handle.net/10400.6/8940.

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Natural flight has always been the source of imagination for the Human being, but reproducing the propulsive systems used by animals is indeed complex. New challenges in today’s society have made biomimetics gain a lot of momentum because of the high performance and versatility these systems possess when subjected to the low Reynolds numbers effects. The present dissertation has as main objective the study of the influence of the number of Reynolds, angle of attack, frequency and amplitude of the movement in the aerodynamic performance of an airfoil NACA0012 that, vertically moves withou
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11

Chang, Che-Cheng, and 張哲誠. "Simulation of Aerodynamic characteristics for dynamic NACA0012 Airfoils." Thesis, 2011. http://ndltd.ncl.edu.tw/handle/58637606704861842279.

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碩士<br>中華大學<br>機械工程學系碩士班<br>99<br>This study investigates the aerodynamics of moving NACA0012 airfoils and wings. The thesis is divided into three parts. First of all, we discuss the the dynamic stall phenomena of oscillating NACA0012 airfoils. To evaluate turbulence effects, three different turbulence models are chosen and compared with the experimental data. The suitable turbulence models are suggested in our studies. In addition, the Force Element Method is applied to evaluate the aerodynamic forces evolutions during the process of unsteady light dynamic stall and deep stall phenomena when
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12

Huang, Shiang-Yu, and 黃翔瑜. "Applying Genetic Algorithm to Find The Maximum Lift to Drag Ratio of NACA0012 Airfoil." Thesis, 2009. http://ndltd.ncl.edu.tw/handle/67892805499638046065.

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碩士<br>中華技術學院<br>飛機系統工程研究所<br>97<br>In this NACA0012 airfoil performance analysis, the flight height is remained the same, and by varying its angle of attack and flight speed, the maximum lift to drag ratio can then be found. Applying the aerodynamic analysis software CFD-ACE+ in cooperation with the Genetic Algorithm toolbox in another software package MATLAB, the optimized performance are obtained. In the Genetic Algorithm process, the elite, crossover and mutation mechanisms are applied in each generation of the process. So it can avoid the local maximum solution, and find the global maximum
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13

Rodrigues, Diana Carvalho. "Visulização e análise das estruturas na esteira de um perfil NACA0012 em movimento oscilatório vertical." Master's thesis, 2020. http://hdl.handle.net/10400.6/10997.

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A biomimética é uma área da ciência que se dedica ao estudo da natureza, tendo por base a sua imitação. Os perfis oscilantes, na natureza, apresentam um alto desempenho propulsivo e, por isso, o ser humano tem desenvolvido um grande interesse nos estudos sobre estas temáticas. Desta forma, este trabalho, no âmbito dos perfis oscilantes, teve por base a visualização, bidimensional, das esteiras libertadas por um perfil NACA0012 sujeito a um movimento puramente vertical, periódico, não sinusoidal, simétrico e assimétrico, a diferentes combinações de velocidade, amplitude e frequência. Os resulta
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14

Mendes, Fábio Miguel Antunes. "Modelação numérica da aerodinâmica de aerofólios para aplicação em turbinas eólicas de pequeno porte." Master's thesis, 2015. http://hdl.handle.net/10316/39002.

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Dissertação de Mestrado Integrado em Engenharia Mecânica apresentada à Faculdade de Ciências e Tecnologia da Universidade de Coimbra.<br>As consequências do uso de combustíveis fósseis pressionam o mundo a adotar fontes de energia renováveis. Neste contexto as turbinas eólicas de eixo vertical de pequeno porte figuram entre uma das alternativas a usar, nomeadamente as turbinas Darrieus. Como em qualquer turbina eólica, nas turbinas Darrieus o perfil das pás tem consequências diretas na sua eficiência, sendo o seu estudo de vital importância. Nesta dissertação são modelados numericamente e
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15

Kirk, Thomas. "The Later Stages of Transition over a NACA0018 Airfoil at a Low Reynolds Number." Thesis, 2014. http://hdl.handle.net/10012/8261.

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The later stages of separated shear layer transition within separation bubbles developing over a NACA0018 airfoil operating at a chord Reynolds number of 105 and at angles of attack of 0, 5, 8, and 10 degrees were investigated experimentally in a wind tunnel. Several experimental tools, including a rake of six boundary-layer hot-wire anemometers, were used to perform measurements over the model. Novel high-speed flow visualization performed with a smoke-wire placed within the separated shear layer showed that roll-up vortices are shed within separation bubbles forming on the suction side of
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16

Babaee, Owlam Babak. "A numerical simulation of flow over a NACA0025 airfoil using Large Eddy Simulation turbulence models." Thesis, 2008. http://spectrum.library.concordia.ca/976118/1/MR40908.pdf.

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The ability of computational fluid dynamic (CFD) to predict critical flow characteristics has always been questionable. Flow separation over lifting surfaces such as airfoils are one of the critical features which can significantly deteriorate their aerodynamic performances. The purpose of this research is to evaluate the accuracy of two CFD methods in predicting the flow separation over a NACA0025 airfoil at low Reynolds numbers. The first code is an in-house code which is based on a 3D compressible Navier-Stokes solver with preconditioning and self-adaptive upwinding methods. The second code
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