Tesis sobre el tema "Aerodynamic angle"
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Wilks, Brett Landon Burkhalter Johnny Evans. "Aerodynamics of wrap-around fins in supersonic flow". Auburn, Ala., 2005. http://repo.lib.auburn.edu/2005%20Fall/Thesis/WILKS_BRETT_54.pdf.
Texto completoFan, Yigang. "Identification of an Unsteady Aerodynamic Model up to High Angle of Attack Regime". Diss., Virginia Tech, 1997. http://hdl.handle.net/10919/29830.
Texto completoPh. D.
Stagg, Gregory A. "An Aerodynamic Model for Use in the High Angle of Attack Regime". Thesis, Virginia Tech, 1998. http://hdl.handle.net/10919/35596.
Texto completoMaster of Science
Sirangu, Vijaya. "AERODYNAMIC CONTROL OF SLENDER BODIES AT HIGH ANGLES OF ATTACK". University of Toledo / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1271365316.
Texto completoSor, Wei Lun. "Aerodynamic Validation of Emerging Projectile Configurations". Thesis, Monterey, California. Naval Postgraduate School, 2012.
Buscar texto completoEver-increasing demands for accuracy and range in modern warfare have expedited the optimization of projectile design. The crux of projectile design lies in the understanding of its aerodynamic properties early in the design phase. This research first investigated the aerodynamic properties of a standard M549, 155mm projectile. The transonic speed region was the focus of the research as significant aerodynamic variation occurs within this particular region. Aerodynamic data from wind tunnel and range testing was benchmarked against modern aerodynamic prediction programs like ANSYS CFX and Aero-Prediction 09 (AP09). Next, a comparison was made between two types of angle of attack generation methods in ANSYS CFX. The research then focused on controlled tilting of the projectile’s nose to investigate the resulting aerodynamic effects. ANSYS CFX was found to provide better agreement with the experimental data than AP09.
Takahama, Morio, Noboru Sakamoto y Yuhei Yamato. "Attitude Stabilization of an Aircraft via Nonlinear Optimal Control Based on Aerodynamic Data". Institute of Electrical and Electronics Engineers, 2009. http://hdl.handle.net/2237/14420.
Texto completoMohmad, Rouyan Nurhana. "Model simulation suitable for an aircraft at high angle of attack". Thesis, Cranfield University, 2016. http://dspace.lib.cranfield.ac.uk/handle/1826/9722.
Texto completoQuickel, Reuben Alexander. "Mount Interference and Flow Angle Impacts on Unshielded Total Temperature Probes". Thesis, Virginia Tech, 2019. http://hdl.handle.net/10919/89952.
Texto completoMaster of Science
Accurately measuring the total temperature of a high-speed fluid flow is a challenging task that is required in many research areas and industry applications. Many methods exist for measuring total temperature, but the use of thermocouple based probes immersed into a flow remains a common and desirable measurement technique. The difficulty in using thermocouple based probes to acquire total temperature stems from attempting to minimize or accurately predict the probe’s measurement error. Conduction, convection, and radiation heat transfer between the fluid flow and probe create challenges for minimizing measurement error so that the accurate total temperature can be obtained. Numerous studies have been performed in prior literature to account for simple cases of each error source. However, there are many complex, practical applications in which the influence of each error source has not been studied. The impacts of a freestream flow angle and the total temperature probe’s mounting structure have not been previously modeled. Both of these effects are very common in gas-turbine applications of total temperature probes. This Thesis will present a fundamental study analyzing the impact that freestream flow angle and a probe’s mount have on a total temperature probe’s measurement error. The influence of conduction and convection heat transfer was studied experimentally for numerous probe geometries, and the impacts of a mounting strut and freestream flow angle were analyzed. A low-order method was developed to predict conduction error and aerodynamic error for total temperature probes in offangle conditions with the presence of mount interference. The developed low-order method was shown to accurately capture the effects of a mounting strut, varying probe geometry, and varying flow angle. Additionally, the low-order method was validated against experimental and 3D, CFD/CHT results.
Lopera, Javier. "Aerodynamic Control of Slender Bodies from Low to High Angles of Attack through Flow Manipulation". Connect to Online Resource-OhioLINK, 2007. http://www.ohiolink.edu/etd/view.cgi?acc_num=toledo1177504352.
Texto completoHammer, Patrick Richard. "A Discrete Vortex Method Application to Low Reynolds Number Aerodynamic Flows". University of Dayton / OhioLINK, 2011. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1311792450.
Texto completoDe, Oliveira Neto Pedro Jose. "An Investigation of Unsteady Aerodynamic Multi-axis State-Space Formulations as a Tool for Wing Rock Representation". Diss., Virginia Tech, 2007. http://hdl.handle.net/10919/29600.
Texto completoPh. D.
LERRO, ANGELO. "Development and Evaluation of Neural Network-Based Virtual Air Data Sensor for Estimation of Aerodynamic Angles". Doctoral thesis, Politecnico di Torino, 2012. http://hdl.handle.net/11583/2518884.
Texto completoMitori, Tiffany Leilani. "Flight and Stability of a Laser Inertial Fusion Energy Target in the Drift Region between Injection and the Reaction Chamber with Computational Fluid Dynamics". DigitalCommons@CalPoly, 2014. https://digitalcommons.calpoly.edu/theses/1154.
Texto completoHubbard, Joshua A. "A study of aerodynamic deaggregation mechanisms and the size control of NanoActive™ aerosol particles". Thesis, Kansas State University, 2006. http://hdl.handle.net/2097/173.
Texto completoDepartment of Mechanical and Nuclear Engineering
Steven J. Eckels
Christopher M. Sorensen
Large specific surface areas and high concentrations of reactive edge and defect sites make NanoActive™ metal oxide powders ideal chemical adsorbents. These powders are dispersed in aerosol form to remediate toxic wastes and neutralize chemical and biological warfare agents. In the destructive adsorption of toxic chemicals, effective application requires particles be as small as possible, thus, maximizing surface area and number of edge and defect sites. Other applications, e.g. smoke clearing, require particles be large so they will settle in a timely manner. Ideally, particle size control could be engineered into powder dispersion devices. The purpose of this study was to explore particle cohesion and aerodynamic deaggregation mechanisms to enhance the design of powder dispersion devices. An aerosol generator and four experimental nozzles were designed to explore the most commonly referenced deaggregation mechanisms: particle acceleration, particles in shear and turbulent flows, and particle impaction. The powders were then dispersed through the nozzles with increasing flow rates. A small angle light scattering device was used to make in situ particle size measurements. The nozzle designed for impaction deaggregated the NanoActive™ MgO particles to a lesser degree than the other three nozzles, which deaggregated the particles to a similar degree. Flows in three of the four nozzles were simulated in a commercial computational fluid dynamics package. Theoretical particle and aggregate stresses from the literature were calculated using simulated data. These calculations suggest particle acceleration causes internal stresses roughly three orders of magnitude larger than shear and turbulent flows. These calculations, coupled with experimental data, lead to the conclusion that acceleration was the most significant cause of particle deaggregation in these experiments. Experimental data also identified the dependence of deaggregation on primary particle size and agglomerate structure. NanoActive™ powders with smaller primary particles exhibited higher resistance to deaggregation. Small primary particle size was thought to increase the magnitude of van der Waals interactions. These interactions were modeled and compared to theoretical deaggregation stresses previously mentioned. In conclusion, deaggregation is possible. However, the ideas of particle size control and a universal dispersion device seem elusive considering the material dependent nature of deaggregation.
Abdeh, Hamed. "Incidence Effects on Aerodynamic and Thermal Performance of a Film-Cooled Gas Turbine Nozzle Guide Vane". Doctoral thesis, Università degli studi di Bergamo, 2018. http://hdl.handle.net/10446/105183.
Texto completoBRANDL, ALBERTO. "Techniques for effective virtual sensor development and implementation with application to air data systems". Doctoral thesis, Politecnico di Torino, 2020. http://hdl.handle.net/11583/2842493.
Texto completoJaitlee, Rajneesh y jaitlee@gmail com. "Mean and Fluctuating Pressures on an Automotive External Rear View Mirror". RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2006. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20070112.125531.
Texto completoClark, Adam. "Predicting the Crosswind Performance of High Bypass Ratio Turbofan Engine Inlets". The Ohio State University, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=osu1476265135449178.
Texto completoFerria, Hakim. "Contribution to Numerical and Experimental Studies of Flutter in Space Turbines. Aerodynamic Analysis of Subsonic or Supersonic Flows in Response to a Prescribed Vibratory Mode of the Structure". Phd thesis, Ecole Centrale de Lyon, 2011. http://tel.archives-ouvertes.fr/tel-00677648.
Texto completoHoang, Ngoc T. "The hemisphere-cylinder at an angle of attack". Diss., This resource online, 1991. http://scholar.lib.vt.edu/theses/available/etd-08062007-094404/.
Texto completoLuke, Mark Elden. "Predicting Drag Polars For Micro Air Vehicles". Diss., CLICK HERE for online access, 2003. http://contentdm.lib.byu.edu/ETD/image/etd297.pdf.
Texto completoVasiljevas, Artūras. "Eksperimentinio akrobatinio lėktuvo skrydžio analizė". Master's thesis, Lithuanian Academic Libraries Network (LABT), 2013. http://vddb.laba.lt/obj/LT-eLABa-0001:E.02~2013~D_20130621_150246-07379.
Texto completoThe thesis examines the aerodynamics of future experimental aerobatic aircraft. Featured in such areas (topics): proper selection of an aircraft wing profile, the required form of the wing, the wing's future performance and parameter estimation, other aircraft parts and their impact on the entire plane dynamics analysis. As analyzed double seated, experimental aerobatic plane in the hope of better indicators selected comparison object double seated acrobatic training plane SU 29. Based on the existing aircraft characteristics and parameters, the conclusions and recommendations will be made.
Petterson, Kristian. "The aerodynamics of slender aircraft forebodies at high angle of attack". Thesis, Cranfield University, 2001. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.392234.
Texto completoCohen, David E. II. "Trim Angle of Attack of Flexible Wings Using Non-Linear Aerodynamics". Diss., Virginia Tech, 1998. http://hdl.handle.net/10919/30404.
Texto completoPh. D.
Pilkington, David J. "Motion induced unsteady aerodynamics at high angles-of-attack". Thesis, University of Bath, 1996. https://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.760689.
Texto completoZakaria, Mohamed Yehia. "Unsteady Nonlinear Aerodynamic Modeling and Applications". Diss., Virginia Tech, 2016. http://hdl.handle.net/10919/79909.
Texto completoPh. D.
Chatlynne, Etan Solomon. "Virtual aero-shaping of a clark-y airfoil at low angles of attack". Thesis, Georgia Institute of Technology, 2001. http://hdl.handle.net/1853/17864.
Texto completoJouannet, Christopher. "Model based aircraft design : high angle of attack aerodynamics and weight estimation methods /". Linköping : Dept. of Mechanical Engineering, Linköping University, 2005. http://www.bibl.liu.se/liupubl/disp/disp2005/tek968s.pdf.
Texto completoWood, Charles Wade. "Oscillating shock impingement on low-angle gas injection into a supersonic flow". Diss., Virginia Tech, 1991. http://hdl.handle.net/10919/39856.
Texto completoMays, Richard Bruce. "Experimental investigation of helium injection at a low downstream angle into supersonic flow". Thesis, Virginia Tech, 1990. http://hdl.handle.net/10919/42076.
Texto completoMaster of Science
Lego, Zachary Michael. "Analysis of High Angle of Attack Maneuvers to Enhance Understanding of the Aerodynamics of Perching". University of Dayton / OhioLINK, 2012. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1355101333.
Texto completoFindlay, David Bruce. "A numerical study of aircraft empennage buffet". Diss., Georgia Institute of Technology, 1999. http://hdl.handle.net/1853/10926.
Texto completoRavi, R. "High Angle of Attack Forebody Flow Physics and Design Emphasizing Directional Stability". Diss., This resource online, 1997. http://scholar.lib.vt.edu/theses/available/etd-01252008-163458/.
Texto completoChiu, Tak Wai. "Aerodynamic loads on a railway train in a cross-wind at large yaw angles". Thesis, University of Cambridge, 1990. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.358612.
Texto completoRavelli, Umberto. "Aerodynamics of a 2017 Formula 1 Car: Numerical Analysis of a Baseline Vehicle and Design Improvements in Freestream and Wake Flows". Doctoral thesis, Università degli studi di Bergamo, 2019. http://hdl.handle.net/10446/128609.
Texto completoTait, Sean William. "An investigation of fore-body aerodynamics during the velocity vector roll". Thesis, University of the West of Scotland, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.265929.
Texto completoWalter, Daniel James y Daniel james walter@gmail com. "Study of aerofoils at high angle of attack in ground effect". RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2007. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20080110.145138.
Texto completoČavoj, Ondřej. "Simulace podmínek ve výpočtech aerodynamiky vozidel". Doctoral thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2019. http://www.nusl.cz/ntk/nusl-403862.
Texto completoLe, Moigne Yann. "Adaptive Mesh Refinement and Simulations of Unsteady Delta-Wing Aerodynamics". Doctoral thesis, KTH, Aeronautical and Vehicle Engineering, 2004. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3786.
Texto completoThis thesis deals with Computational Fluid Dynamics (CFD)simulations of the flow around delta wings at high angles ofattack. These triangular wings, mainly used in militaryaircraft designs, experience the formation of two vortices ontheir lee-side at large angles of attack. The simulation ofthis vortical flow by solving the Navier-Stokes equations isthe subject of this thesis. The purpose of the work is toimprove the understanding of this flow and contribute to thedesign of such a wing by developing methods that enable moreaccurate and efficient CFD simulations.
Simulations of the formation, burst and disappearance of thevortices while the angle of attack is changing are presented.The structured flow solver NSMB has been used to get thetime-dependent solutions of the flow. Both viscous and inviscidresults of a 70°-swept delta wing pitching in anoscillatory motion are reported. The creation of the dynamiclift and the hysteresis observed in the history of theaerodynamic forces are well reproduced.
The second part of the thesis is focusing on automatic meshrefinement and its influence on simulations of the delta wingleading-edge vortices. All the simulations to assess the gridquality are inviscid computations performed with theunstructured flow solver EDGE. A first study reports on theeffects of refining thewake of the delta wing. A70°-swept delta wing at a Mach number of 0.2 and an angleof attack of 27° where vortex breakdown is present abovethe wing, is used as testcase. The results show a strongdependence on the refinement, particularly the vortex breakdownposition, which leads to the conclusion that the wake should berefined at least partly. Using this information, a grid for thewing in the wind tunnel is created in order to assess theinfluence of the tunnel walls. Three sensors for automatic meshrefinement of vortical flows are presented. Two are based onflow variables (production of entropy and ratio of totalpressures) while the third one requires an eigenvalue analysisof the tensor of the velocity gradients in order to capture theposition of the vortices in the flow. These three vortexsensors are successfully used for the simulation of the same70° delta wing at an angle of attack of 20°. Acomparison of the sensors reveals the more local property ofthe third one based on the eigenvalue analysis. This lattertechnique is applied to the simulation of the wake of a deltawing at an angle of attack of 20°. The simulations on ahighly refined mesh show that the vortex sheet shed from thetrailing-edge rolls up into a vortex that interacts with theleading-edge vortex. Finally the vortex-detection technique isused to refine the grid around a Saab Aerosystems UnmannedCombat Air Vehicle (UCAV) configuration and its flight dynamicscharacteristics are investigated.
Key words:delta wing, high angle of attack, vortex,pitching, mesh refinement, UCAV, vortex sensor, tensor ofvelocity gradients.
Lewis, Daniel Joseph. "Tip clearance and angle of attack effects upon the unsteady response of a vibrating flat plate in crossflow /". This resource online, 1993. http://scholar.lib.vt.edu/theses/available/etd-06112009-063924/.
Texto completoKo, Joon Soo. "Analysis of the dynamic stability derivatives for high angle of attack aircraft". Diss., Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/52300.
Texto completoPh. D.
Frink, William D. "Hot-wire surveys in the vortex wake downstream of a three-percent fighter aircraft model at high angles of attack". Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA241869.
Texto completoThesis Advisor(s): Hebbar, Sheshagiri K. ; Platzer, Max F. "December 1990." Description based on title screen as viewed on March 31, 2010. DTIC Identifier(s): Trailling Vortices, Wake, Trubulent Flow, Jet Fighters, High Alpha (High Angle of Attack), Vortex Wake, Angle of Attack, Extendable Structures, Leading Edges, Fences, Lex Fences, Wind Tunnel Models, F-17 Aircraft, F/A-18 Aircraft, Wind Tunnel Tests, Hot Wire Anemometers, Theses. Author(s) subject terms: High Angle-of-Attack Aerodynamics, Hot-Wire Measurements, Wind Tunnel Studies. Includes bibliographical references (p. 24-25). Also available in print.
Cavazos, Odilon V. "A flow visualization study of LEX generated vortices on a scale model of F/A-18 fighter aircraft at high angles of attack". Monterey, California : Naval Postgraduate School, 1990. http://handle.dtic.mil/100.2/ADA236534.
Texto completoThesis Advisor(s): Hebbar, S. K. ; Platzer, M. F. "June 1990." Description based on title screen as viewed on October 19, 2009. DTIC Descriptor(s): Angles, yaw, scale models, attack, motion, rates, moments, vortices, flow visualization, rupture, asymmetry, aerodynamic forces, leading edges, range(distance), statics, hysteresis, aerodynamics, high angles, pitch(motion). DTIC Indicator(s): Flow visualization, trailing vortices, F/A-18 aircraft. Author(s) subject terms: High angle of attack aerodynamics, effect of pitch rate and yaw, vortex development and bursting, flow visualization by dye injection, water tunnel studies, F/A-18 fighter aircraft. Includes bibliographical references (p. 44-45). Also available in print.
Desenfans, Philip. "Aerodynamics of the Maple Seed". Aircraft Design and Systems Group (AERO), Department of Automotive and Aeronautical Engineering, Hamburg University of Applied Sciences, 2019. http://d-nb.info/1204982848.
Texto completo東, 大輔, Daisuke AZUMA, 佳朗 中村 y Yoshiaki NAKAMURA. "前縁回転/後縁ジェットハイブリッド法によるデルタ翼揚力増加". 日本航空宇宙学会, 2006. http://hdl.handle.net/2237/13878.
Texto completoSchaeffler, Norman Walter. "All The King's Horses: The Delta Wing Leading-Edge Vortex System Undergoing Vortex Breakdown: A Contribution to its characterization and Control under Dynamic Conditions". Diss., Virginia Tech, 1998. http://hdl.handle.net/10919/30454.
Texto completoPh. D.
Липовий, Віталій Миколайович, Виталий Николаевич Липовый y Vitalii Mykolaiovych Lypovyi. "Підвищення енергетичних показників ортогональних вітродвигунів для використання вітрових потоків малої потужності". Thesis, Вид-во СумДУ, 2015. http://essuir.sumdu.edu.ua/handle/123456789/40886.
Texto completoДиссертация на соискание ученой степени кандидата технических наук по специальности 05.05.17 - гидравлические машины и гидропневмоагрегаты. - Сумской государственный университет, Сумы, 2015. В диссертационной работе приведены решения вопроса самозапуска вертикально-осевого ветродвигателя для малых и средних размеров ветроколес при использовании ветровых потоков низких мощностей. Разработан аналитический метод определения оптимальных характеристик потока воздуха для возникновения максимального тягового усилия на всей траектории движения лопасти. Численным моделированием обтекания лопасти потоком воздуха решен вопрос определения аэродинамических коэффициентов для заданного профиля, что с определенным предположением позволяет отказаться от натурного эксперимента продувки профиля в аэродинамической трубе. Предложен механизм влияния на ортогональное ветроколесо путем введения вспомогательного вектора скорости с целью повышения его энергетических характеристик. Данный механизм испытано на экспериментальном стенде и доказана целесообразность его использования при работе ветроколеса на нерасчетных режимах. Впервые разработано двухструйную математическую модель ортогонального ветродвигателя для определения кинематических характеристик потока воздуха, которые влияют на повышение мощности ветроколеса. Разработано аналитические зависимости для определения влияния на эффективность работы ветротурбины дополнительного вектора скорости W̅', что приводит к смещению треугольников скоростей в сторону увеличения тяговой силы на поверхности лопасти. В результате исследований определены показатели крутящих моментов на валу ортогональной ветротурбины с прямыми лопастями парусного типа. Доказано повышение стартового тягового момента. Для предложенных конструкций симметричных гибких профилированных лопастей приведены интегральные характеристики при переменных геометрических показателях ветроколеса. Экспериментальным путем определено, что введение вспомогательного вектора скорости путем установки экрана на дуге круговой траектории в области нулевого азимутального угла β=0 позволяет повысить мощность ветроколеса. Плоский экран длинной 120 мм, наклоненный под углом 20° на азимутальном угле 36° повышает генерируемую мощность ветроколеса в 2,5 раза. Определено, что использование гибких парусных лопастей симметричного профиля позволяет получить высокие значения начального крутящего момента на валу ортогональной ветротурбины. При низкой быстроходности θ ˂ 0,5 значение коэффициента крутящего момента составляет Cm = 0,47. При дальнейшем разгоне ветроколеса Cm падает до значения жесткой симметричной лопасти C m = 0,1. Результаты диссертационной работы позволяют разрабатывать высокоэффективные ветроэнергетические установки, ориентированные на использование ветровых потоков низкой мощности, что актуально для территории Украины.
Thesis for the degree of candidate of technical sciences, specialty 05.05.17 - hydraulic machines and hydropneumaticunits. – Sumy State University, Sumy, 2015. The thesis shows the solution to the question of self-start of vertical-axis wind turbine for small and medium-sized windwheels using wind currents low capacity. An analytical method for determining the optimal characteristics of the air flow for the occurrence of maximum power to the entire trajectory of the blade. Numerical simulation of flow around the blade airflow resolved the question of determining the aerodynamic coefficients for a given profile, with certain assumptions eliminates the natural experiment blowing in the wind tunnel profile. The mechanism of the effect of the orthogonal wind wheel, by introducing auxiliary velocity vector, in order to improve its energy performance. This mechanism is tested on experimental stand and prove the feasibility of its use in the operation of the wind wheel on the off-nominal conditions. The studies identify indicators torque of the orthogonal wind turbine with straight blades sailing type. Proven to increase the starting of torque. For the proposed construction of symmetric flexible profiled blades are given integral characteristics with variable geometry have been the propeller. The results of the thesis allow you to develop highly efficient wind turbines focused on the use of wind flows low power, which is important for Ukraine.
Jirásek, Lukáš. "Analýza vlivu polohy karoserie závodního vozu na aerodynamické charakteritiky". Master's thesis, Vysoké učení technické v Brně. Fakulta strojního inženýrství, 2011. http://www.nusl.cz/ntk/nusl-229397.
Texto completoLee, Jaewoo. "Efficient inverse methods for supersonic and hypersonic body design, with low wave drag analysis". Diss., Virginia Tech, 1991. http://hdl.handle.net/10919/37406.
Texto completoPh. D.
Lewis, Daniel Russell. "Tip clearance and angle of attack effects upon the unsteady response of a vibrating flat plate in crossflow". Thesis, Virginia Tech, 1993. http://hdl.handle.net/10919/43198.
Texto completoThe influence of tip clearance and angle of attack upon the mid-span unsteady pressure response of a vibrating flat plate was investigated experimentally. Unsteady pressure measurements were taken for a variety of incidence angles, vibration frequencies and tip clearances over a Mach number range of 0.2 to 0.6.
It was found that changes in tip clearance had an effect on measured pressure fluctuations at higher angles of attack and larger Mach numbers. It was also observed that the amplitude of the unsteady pressure increased as the incidence angle was increased.
The plate was mechanically induced to oscillate in translation, simulating the flISt bending mode. Averaged Fast Fourier Transforms were used to determine pressure oscillation amplitudes and phase lags with respect to the plate motion.
Master of Science