Дисертації з теми "Transonic tunnel"
Оформте джерело за APA, MLA, Chicago, Harvard та іншими стилями
Ознайомтеся з топ-25 дисертацій для дослідження на тему "Transonic tunnel".
Біля кожної праці в переліку літератури доступна кнопка «Додати до бібліографії». Скористайтеся нею – і ми автоматично оформимо бібліографічне посилання на обрану працю в потрібному вам стилі цитування: APA, MLA, «Гарвард», «Чикаго», «Ванкувер» тощо.
Також ви можете завантажити повний текст наукової публікації у форматі «.pdf» та прочитати онлайн анотацію до роботи, якщо відповідні параметри наявні в метаданих.
Переглядайте дисертації для різних дисциплін та оформлюйте правильно вашу бібліографію.
Jones, Gregory Stephen. "The measurement of wind tunnel flow quality at transonic speeds." Diss., Virginia Tech, 1991. http://hdl.handle.net/10919/39109.
Повний текст джерелаPh. D.
Rosson, Joel Christopher. "Dynamic flow quality measurements in a transonic cryogenic wind tunnel." Thesis, Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/101463.
Повний текст джерелаM.S.
Neal, Graeme. "Three-dimensional model testing in the transonic self-streamlining wind tunnel." Thesis, University of Southampton, 1988. https://eprints.soton.ac.uk/52257/.
Повний текст джерелаGriffith, Dwaine O. "Turbulence measurements and noise generation in a transonic cryogenic wind tunnel." Thesis, Virginia Tech, 1989. http://hdl.handle.net/10919/45979.
Повний текст джерелаA high-frequency combination probe was used to measure dynamic flow quality in the test section of the NASA Langley 0.3-m Transonic Cryogenic Tunnel. The probe measures fluctuating stagnation (total) temperature and pressure, static pressure, and flow angles in two orthogonal planes. Simultaneous unsteady temperature and pressure measurements were also made in the settling chamber of the tunnel. The data show that the stagnation temperature fluctuations remain constant, and the stagnation pressure fluctuations increase by a factor of two, as the flow accelerates from the settling chamber to the test section. In the test section, the maximum rms value of the normalized fluctuating velocity is 0.7 percent. Correlation coefficients l failed to show vortlcity, entropy, or sound as the dominant mode of turbulence in the tunnel.
At certain tunnel operating conditions, periodic disturbances are seen in the data taken in the test section. A possible cause for the disturbances is found to be acoustic coupling of the test section and plenum chamber via the perforated side walls in the tunnel. The experimental data agree well with the acoustic coupling theory.
Master of Science
Suratanakavikul, Varangrat. "Computational study of compressible flow in an S-shaped duct." Thesis, Imperial College London, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.313370.
Повний текст джерелаJeffries, Michael. "Initial investigations of transonic turbine aerodynamics using the Carleton University high-speed wind tunnel." Thesis, National Library of Canada = Bibliothèque nationale du Canada, 2001. http://www.collectionscanada.ca/obj/s4/f2/dsk3/ftp04/NQ60956.pdf.
Повний текст джерелаBailey, Matthew Marlando. "An Extended Calibration and Validation of a Slotted-Wall Transonic Wall-Interference Correction Method for the National Transonic Facility." Diss., Virginia Tech, 2019. http://hdl.handle.net/10919/95882.
Повний текст джерелаDoctor of Philosophy
The purpose of conducting experimental tests in wind tunnels is often to acquire a quantitative measure of test article aerodynamic characteristics in such a way that those specific characteristics can be accurately translated into performance characteristics of the real vehicle that the test article intends to simulate. The difficulty in accurately simulating the real flow problem may not be readily apparent, but scientists and engineers have been working to improve this desired equivalence for the better part of the last half-century. The primary aspects of experimental aerodynamics simulation that present difficulty in attaining equivalence are: geometric fidelity, accurate scaling, and accounting for the presence of walls. The problem of scaling has been largely addressed by adequately matching conditions of similarity like compressibility (Mach number), and viscous effects (Reynolds number). However, accounting for the presence of walls in the experimental setup has presented ongoing challenges for ventilated boundaries; these challenges include difficulties in the correction process, but also extend into the determination of correction uncertainties. Exploiting a previously designed statistical validation method, this effort accomplishes the extension of a calibration and validation effort for a boundary pressure wall interference corrections method. The foundational calibration and validation work was based on blockage interference only, while this present work extends the assessment of the method to encompass blockage and lift interference production. The validation method involves the establishment of independent cases that are then compared to rigorously determine the degree to with the correction method can converge free-air solutions for differing interference scenarios. The process involved first establishing an empty-tunnel calibration to gain both a centerline Mach profile of the facility at various ventilation settings, and to gain a baseline wall pressure signature undisturbed by a test article. The wall boundary condition parameters were then calibrated with a blockage and lift interference producing test article, and final corrected performance coefficients were compared for varying test section ventilated configurations to validate the corrections process and assess its domain of applicability. During the validation process discrimination between homogeneous and discrete implementations of the boundary condition was accomplished and final results indicated comparative strength in the discrete implementation's ability to capture experimental flow physics. Final results indicate that a discrete implementation of the General Slotted Wall boundary condition is effective in significantly reducing variations caused by differing interference fields. Corrections performed with the discrete implementation of the boundary condition collapse differing measurements of lift coefficient to within 0.0027, drag coefficient to within 0.0002, and pitching moment coefficient to within 0.0020.
Hatchett, John Henry. "An Investigation of Effectiveness of Normal and Angled Slot Film Cooling in a Transonic Wind Tunnel." Thesis, Virginia Tech, 2008. http://hdl.handle.net/10919/31324.
Повний текст джерелаMaster of Science
Doig, Graham Mechanical & Manufacturing Engineering Faculty of Engineering UNSW. "Compressible ground effect aerodynamics." Awarded by:University of New South Wales. Mechanical & Manufacturing Engineering, 2009. http://handle.unsw.edu.au/1959.4/44696.
Повний текст джерелаBoyd, Robert Raymond. "An Experimental and Computational Investigation on the Effect of Transonic Flow in Hypersonic Wind Tunnel Nozzles, Including Filtered Rayleigh Scattering Measurements /." The Ohio State University, 1996. http://rave.ohiolink.edu/etdc/view?acc_num=osu148793364864785.
Повний текст джерелаDumon, Jéromine. "Etude expérimentale et numérique du phénomène de tremblement transsonique sur un profil diamant." Thesis, Toulouse, ISAE, 2020. http://www.theses.fr/2020ESAE0009.
Повний текст джерелаThe development of reusable space launchers requires a comprehensive knowledge oftransonic flow effects on the launcher structure, such as buffet. Indeed, the mechanicalintegrity of the launcher can be compromised by shock wave/boundary layer interactions.These interactions can induce, amongst others, lateral forces responsible for rolling andpitching moments, or modal excitation of some structural elements that can lead to theirdamage or even failure. This work reports numerical and experimental investigationson the characterization of the transonic flow past a diamond airfoil, designed fornanosatellite-dedicated launchers, with a particular interest for buffeting. Buffeting hasbeen extensively studied. Unfortunately, the detailed mechanisms that are responsiblefor the buffet inception and its dynamics are still debated. Moreover, there is a lackof studies for diamond airfoils. Here, time-resolved Schlieren visualizations, steadyand unsteady pressure measures and LVD measures are experimentally conducted ina transonic wind tunnel. They are compared with numerical predictions based on un-steady RANS and LES approaches. Three dimensional features of buffet over a diamondairfoil without swept, and the occurrence of a chaotic state, are experimentally highlighted
Tanner, Christopher Lee. "Aeroelastic analysis and testing of supersonic inflatable aerodynamic decelerators." Diss., Georgia Institute of Technology, 2012. http://hdl.handle.net/1853/47534.
Повний текст джерелаZaccaria, Michael A. "Development of a transonic turbine cascade facility." Thesis, Virginia Polytechnic Institute and State University, 1988. http://hdl.handle.net/10919/53201.
Повний текст джерелаMaster of Science
Villafañe, Roca Laura. "Experimental Aerothermal Performance of Turbofan Bypass Flow Heat Exchangers." Doctoral thesis, Universitat Politècnica de València, 2014. http://hdl.handle.net/10251/34774.
Повний текст джерелаVillafañe Roca, L. (2013). Experimental Aerothermal Performance of Turbofan Bypass Flow Heat Exchangers [Tesis doctoral no publicada]. Universitat Politècnica de València. https://doi.org/10.4995/Thesis/10251/34774
TESIS
Popernack, Thomas G. Jr. "Development of a data reduction method for a high frequency angle probe." Thesis, Virginia Tech, 1987. http://hdl.handle.net/10919/45881.
Повний текст джерелаA data reduction method has been developed and tested for a high frequency angle probe. The angle probe is designed for unsteady aerodynamic measurements in transonic cryogenic wind tunnels. The probe measures time-resolved total pressure, static pressure, angle of attack, and yaw angle from readings of four pressure transducers. The unique feature of this probe, as compared to a conventional multi-hole directional probe, is that the four high frequency response silicon pressure transducers are mounted flush on the probe tip. The data reduction method is basically an interpolation routine of calibration curves. The calibration curves consist of experimentally determined non-dimensional flow coefficients.
Two experiments were conducted to test the probe and the data reduction method.
The first experiment tested the angle probe in a Karman vortex street shed from a cylinder.
In the second experiment, the angle probe was placed in an open air jet with an
exit Mach number of 0.42. Plots of the time-resolved measurements and the Fast
Fourier Transform analysis were made for each test.
Master of Science
Chyan, Yeu-Liang, and 錢禹良. "The Calibration of a Pilot Transonic Wind Tunnel." Thesis, 1996. http://ndltd.ncl.edu.tw/handle/20952361553067321824.
Повний текст джерела國立成功大學
航空太空工程學系
84
The objective of this work is to calibrate the transonic pilot tunnel located in ASTRC. The calibration process basically follows that of the large transonic tunnel built by Fluidyne. Various operational parameters were studied which include settling chamber stagnation pressure, wall porosity, Mach flap angle, choke flap angle and the test section wall divergence angle. How do these parameters affect the flow quality were assessed by measuring the centerline Mach number distributions as the control mechanism associated with each parameter was activated. Aside from these tunnel control parameters, the deviation of plenum chamber Mach number to the centerline Mach number was considered important also. All the Mach numbers obtained were calculated using the measured static pressure and the settling chamber stagnation pressure via an isentropic relationship. The calibration results show that the wall effects are significant for high-speed flow and the test section flow speed can be accelerated when either Mach flap or test section wall angle was enlarged. The twice deviation in centerline Mach number was found to be around 0.004∼0.006 for low speed flow(M=0.3∼0.7) and 0.006∼ 0.011 for high speed flow(M=0.7∼1.1), respectively. Generally speaking, a larger Mach number test section flow will cause a larger deviation in the centerline Mach number distribution.
Yeh, Jiunn-Shyan, and 葉俊賢. "Calibration of the ASTRC/NCKU Transonic Wind Tunnel." Thesis, 1994. http://ndltd.ncl.edu.tw/handle/49852742771140415878.
Повний текст джерела國立成功大學
航空太空工程學系
82
The purpose of the study is to calibrate the flow quality of the ASTRC/TWT. The calibration included the flow uniformity (M_rms/Mcl), a parameter DM, and the aerodynamic noise level (Δ Cp). In studying the flow uniformity and the DM parameter, the centerline pipes were used to measure the static pressure distribution at the centerline of the wind tunnel. In studying the aerodynamic noise, four pressure transducers were flush- mounted on the 10-degree cone model which was used as the standard model to measure the aerodynamic noise in different flow condition. We used the technique of power spectrum analysis to identify the frequency components of the noise. The results showed that M_rms/Mcl is less than 0.005 with suitable parameter (MF,τ,θw) settings at subsonic. On the other hand, the flow quality at supersonic is inferior to that at subsonic. In the study of aerodynamic noise both the noise level (ΔCp) measured on the wall and 10-degree cone show the same trend. At M=0.8 or 0.9 the power spectrum results wind tunnel structure is about 159Hz. At M=0.8 or 0.9, varing the wall porosity of the test section wall show significant effect on the noise level of the test section.
Chang, Kuo-Chih, and 張國治. "Wind-Tunnel Investigation on Aerodynamic Characteristics of Transonic Wings." Thesis, 1996. http://ndltd.ncl.edu.tw/handle/95884615209757635585.
Повний текст джерелаNash, Jonathan. "Design, construction and calibration of a transonic wind tunnel." Thesis, 2013. http://hdl.handle.net/10539/12351.
Повний текст джерелаHE, LONG-ZONG, and 賀榮宗. "Transonic wind tunnel wall interference assessment using viscous/inviscid interaction method." Thesis, 1993. http://ndltd.ncl.edu.tw/handle/76650553671853782029.
Повний текст джерелаHSIAU, WEI-JIUNN, and 蕭偉駿. "THE DESIGN,MANUFACTURING AND CALIBRATION OF A PILOT TRANSONIC WIND TUNNEL (II)." Thesis, 1994. http://ndltd.ncl.edu.tw/handle/58945303802038288966.
Повний текст джерелаChang, Cheng-Jen, and 張政仁. "The Design, Manufacturing and Calibration of a Pilot Transonic Wind Tunnel (I)." Thesis, 1994. http://ndltd.ncl.edu.tw/handle/76005644355955038656.
Повний текст джерелаChou, Ta-Wei, and 周大偉. "A Study on 2-D Wall Interference of a Transonic Wind Tunnel." Thesis, 1999. http://ndltd.ncl.edu.tw/handle/06239324829963134183.
Повний текст джерела國立成功大學
航空太空工程學系
87
The phenomenon of wind tunnel wall interference is due to the presence of the wall of wind tunnel test section. Consequently the flow field around a testing model situated in the test section of wind tunnel is normally somewhat different from that corresponding to the free-flight condition. With the use of ventilated walls for transonic wind tunnel, the interference problem becomes even more complex. The purpose of this study is to investigate the subsonic wall interference due to the presence of 2-D perforated walls of a transonic wind tunnel in ASTRC, NCKU. The porosity parameter method was employed to study the interference effect. This method was deduced from the linear potential flow theory subject to the concern of perforated walls. Experiments were made for a NACA0012 airfoil, that pressure distributions on the airfoil at Mach numbers from 0.3 to 0.8 and angles of attack from to were obtained. In addition, experiments on the effect of Mach flap position to wall interference were made at M=0.3. Base on the data of pressure distributions obtained, the aerodynamic coefficients were then calculated. Comparing the results obtained with the reference aerodynamic coefficients of NACA0012 lead us to suggest a formula to correct the interference effect of our wind tunnel. The results show that the formula proposed is able to adjust the aerodynamic coefficients measured to the reference data at low Mach number and low-AOA. But at high subsonic or high-AOA, this formula does not give satisfactory result.
Lee, Chia-Fong, and 李佳峰. "The Application of Liquid Crystal and Pressure Sensitive Paint in Transonic Wind Tunnel Experiment." Thesis, 2002. http://ndltd.ncl.edu.tw/handle/282gtw.
Повний текст джерела國立成功大學
航空太空工程學系碩博士班
90
The purpose of this study is to develop the measurement techniquesusing pressure sensitive paint (PSP) and liquid crystal for transonic wind tunnel experiment. Acquiring temperature and pressure distribution of modelsurface is very important for studying the flow phenomena associated with theaerodynamic performance of the model. Traditional temperature and pressure measurements are taken with temperature sensors and pressure taps embedded in the model surface. Temperature and pressure taps do not give good spatial resolution due to the need for individual sensors. If the shape of the model is too small or complicated in geometry, it will limit the quantity of the sensors.Also, making a model can be very expensive if installation of a large amount of taps or sensors has to be considered. Using PSP and liquid crystal techniques, one can acquire temperature and pressure distributions,respectively, with high spatial resolution and simple model preparation. This research includes two parts. (1) Develop the PSP technique with the qualitative and quantitative analysis, and apply the technique in transonic wind tunnel experiment, with the aim to investigate the phenomena of flow around an ogive body at angles of attack. (2) Apply the liquid crystal technique in the transonic wind tunnel experiments, for studying the surface patterns concerning a finite cylinder on a flat plate and an ogive body. Attempts are made to reduce the temperature distributions from the obtained liquid crystal images.
Risius, Steffen. "Development of a time-resolved quantitative surface-temperature measurement technique and its application in short-duration wind tunnel testing." Thesis, 2018. http://hdl.handle.net/11858/00-1735-0000-002E-E44D-A.
Повний текст джерела