Relevant bibliographies by topics / Aerodynamic pressure

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  2. Dissertations / Theses
  3. Books
  4. Book chapters
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Academic literature on the topic 'Aerodynamic pressure'

Author: Grafiati
Published: 4 June 2021
Last updated: 9 June 2025

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Journal articles on the topic "Aerodynamic pressure"

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Xie, Dan, Min Xu, Honghua Dai, and Tao Chen. "New Look at Nonlinear Aerodynamics in Analysis of Hypersonic Panel Flutter." Mathematical Problems in Engineering 2017 (2017): 1–13. http://dx.doi.org/10.1155/2017/6707092.

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A simply supported plate fluttering in hypersonic flow is investigated considering both the airflow and structural nonlinearities. Third-order piston theory is used for nonlinear aerodynamic loading, and von Karman plate theory is used for modeling the nonlinear strain-displacement relation. The Galerkin method is applied to project the partial differential governing equations (PDEs) into a set of ordinary differential equations (ODEs) in time, which is then solved by numerical integration method. In observation of limit cycle oscillations (LCO) and evolution of dynamic behaviors, nonlinear aerodynamic loading produces a smaller positive deflection peak and more complex bifurcation diagrams compared with linear aerodynamics. Moreover, a LCO obtained with the linear aerodynamics is mostly a nonsimple harmonic motion but when the aerodynamic nonlinearity is considered more complex motions are obtained, which is important in the evaluation of fatigue life. The parameters of Mach number, dynamic pressure, and in-plane thermal stresses all affect the aerodynamic nonlinearity. For a specific Mach number, there is a critical dynamic pressure beyond which the aerodynamic nonlinearity has to be considered. For a higher temperature, a lower critical dynamic pressure is required. Each nonlinear aerodynamic term in the full third-order piston theory is evaluated, based on which the nonlinear aerodynamic formulation has been simplified.
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Qi, Xiaojing, Yuxin Ou, Hance Zhang, and Da Wang. "Efficiency Enhancement Design Approach in the Side Wing of a FSAE Car Utilizing a Shutter-Like Fairing Structure." Applied Sciences 12, no. 13 (June 28, 2022): 6552. http://dx.doi.org/10.3390/app12136552.

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Aerodynamical design is one of the critical technologies in race car engineering, and favorable race car aerodynamics is supposed to provide sufficient negative lift force and keep the center of pressure in the vicinity of center of mass. Taking the Formula Society of Automotive Engineers (FSAE) cars as an example, side wing structure is frequently adopted for better grip in the mid-back of short wheelbase, open wheel race cars. This research designs a shutter-like fairing structure and utilizes it to weaken the vorticity and reinforce the pressure of side wing flow field. The sensitivity of side wing aerodynamic efficiency to shutters’ key parameters is analyzed, and optimized shutters’ key parameters for a prototype FSAE race car are obtained through computational fluid dynamics simulations. Results indicate that over 10% enhancement in side wing aerodynamic efficiency can be achieved by applying optimized shutters.
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Jing, Haiquan, Xiaoyu Ji, Xuhui He, Shifeng Zhang, Jichao Zhou, and Haiyu Zhang. "Dynamic Characteristics of Unsteady Aerodynamic Pressure on an Enclosed Housing for Sound Emission Alleviation Caused by a Passing High-Speed Train." Applied Sciences 12, no. 3 (January 31, 2022): 1545. http://dx.doi.org/10.3390/app12031545.

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Train speed is increasing due to the development of high-speed railway technology. However, high-speed trains generate more noise and discomfort for residents, enclosed housing for sound emission alleviation is needed to further reduce noise. Because these enclosed housings for sound emission alleviation restrain the air flow, strong and complicated aerodynamic pressures are generated inside the housing for sound emission alleviation when a train passes through at a high speed. This train-induced aerodynamic pressure, particularly its dynamic characteristics, is a key parameter in structural design. In the present study, the train-induced unsteady aerodynamic pressure in an enclosed housing for sound emission alleviation is simulated using the dynamic mesh method, and the dynamic characteristics of the aerodynamic pressure are investigated. The simulation results show that when the train is running in the enclosed housing for sound emission alleviation, the unsteady aerodynamic pressure is complicated and aperiodic, and after the train leaves the housing for sound emission alleviation, the aerodynamic pressure reverts to periodic decay curves. Two new terms, the duration of the extreme aerodynamic pressure and the pressure change rate, are proposed to evaluate the dynamic characteristics when the train passes through the barrier. The dominant frequency and decay rate are adopted to express the dynamic characteristics after the train exits. When the train runs in the enclosed housing for sound emission alleviation, the longest durations of the positive and negative extreme aerodynamic pressures are in the middle section, and the maximum change rate of aerodynamic pressure occurs at the entrance area. After the train exits the housing for sound emission alleviation, the pressure amplitude at the central region is always higher than those close to the entrance/exit. The dominant frequency of the aerodynamic pressure is identified and explained using wave propagation theory, the decay rate of the aerodynamic pressure at all sections is close.
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Junaidin, Buyung. "AERODYNAMIC ANALYSIS OF SPORT UTILITY VEHICLE (SUV) BY COMPUTATIONAL FLUID DYNAMICS (CFD) APROACH." Vortex 3, no. 1 (January 15, 2022): 67. http://dx.doi.org/10.28989/vortex.v3i1.1161.

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The main purpose of aerodynamics analysis of a vehicle is optimizing it’s form to increase aerodynamics efficiency. More streamline of aerodynamic design of a vehicle not just effecting to lower fuel consumption which is cause by lower drag due to wind at highspeed, but also increasing stability dan control of the vehicle itself. The vehicles are existed with many variations of form so they have difference aerodynamic characteristics. For a personal vehicle like cars, have many variants such as sedan, sport utility vehicle (SUV), multipurposes utility vehicle (MPV), ect. It becomes a motivation to do research about aerodynamic analysis of a SUV car which is a car variant with huge utilize in Indonesia. In this research, aerodynamic characteristics of SUV car are evaluated by computational simulation with computational fluid dynamics (CFD) approach. CFD simulation yields aerodynamic characteristics data and flow behaviors around car model. Simulation results show that critical drag coefficient (CDcrit) of SUV car is 0.36 with lift coefficient is 0.25. the CDcrit of the car is lower than typical value for a modern car. So that, optimalization of SUV car form which analyzed is needed. Contours of pressure at car surfaces show that high pressure area are located at front of grill and windshield, and low-pressure area are located at nose and leading-trailing roof due to the form nose and leading-trailing roof are streamlines. At back surface of the car, low pressure area are formed by flow separation which creates wake.
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Zhang, Cheng Chun, Wen Qiang Wang, Lei Shi, Jing Wang, and Lu Quan Ren. "Experimental and Numerical Study on Aerodynamic Noise Reduction of Cylindrical Rod with Bionic Wavy Surface." Applied Mechanics and Materials 461 (November 2013): 690–701. http://dx.doi.org/10.4028/www.scientific.net/amm.461.690.

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Inspired by the non-smooth structure of the leading edge of owls wing,a bionic wavy cylindrical surface is proposed in this paper to reduce the aerodynamic noise of a cylindrical rod. The effects of bionic wavy surface on the aerodynamic and aeroacoustic performance of the cylinder are investigated by wind tunnel and numerical simulation. The fluctuating pressure of the smooth cylinder and the bionic wavy surface cylinder are tested by pulsating pressure sensors in FD-09 low speed wind tunnel of China Aerospace Aerodynamics Research Institute. The fluctuating pressure of the bionic wavy surface cylinder is significantly lower than that of the smooth cylinder. We used the software ANSYS FLUENT to research the effect of the bionic wavy surface on the aerodynamic characteristics and aerodynamic noise of a cylinder by the Large Eddy Simulation (LES) and the Ffowcs Williams and Hawkings (FW-H) equation. Compared with the smooth cylinder, the aerodynamic noise of the bionic wavy cylinder is reduced by 6.7dB. A study of the relationship between the fluctuating lift and the aerodynamic noise size is conducted. We found that the sound pressure level of the wavy surface cylinder is significantly lower when the lift fluctuation amplitude decreased. Bionic wavy surface can effectively restrain the separated shear layer transition to turbulence. The frequency of vortex shedding which causes the lift fluctuations is reduced, so the aerodynamic noise of the circular cylinder is reduced. Keywords: bionics, cylindrical rod, wavy surface, aerodynamic noise, flow control
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Sun, Xiaoqi, and Han Xiao. "Numerical Modeling and Investigation on Aerodynamic Noise Characteristics of Pantographs in High-Speed Trains." Complexity 2018 (2018): 1–12. http://dx.doi.org/10.1155/2018/6932596.

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Pantographs are important devices on high-speed trains. When a train runs at a high speed, concave and convex parts of the train cause serious airflow disturbances and result in flow separation, eddy shedding, and breakdown. A strong fluctuation pressure field will be caused and transformed into aerodynamic noises. When high-speed trains reach 300 km/h, aerodynamic noises become the main noise source. Aerodynamic noises of pantographs occupy a large proportion in far-field aerodynamic noises of the whole train. Therefore, the problem of aerodynamic noises for pantographs is outstanding among many aerodynamics problems. This paper applies Detached Eddy Simulation (DES) to conducting numerical simulations of flow fields around pantographs of high-speed trains which run in the open air. Time-domain characteristics, frequency-domain characteristics, and unsteady flow fields of aerodynamic noises for pantographs are obtained. The acoustic boundary element method is used to study noise radiation characteristics of pantographs. Results indicate that eddies with different rotation directions and different scales are in regions such as pantograph heads, hinge joints, bottom frames, and insulators, while larger eddies are on pantograph heads and bottom frames. These eddies affect fluctuation pressures of pantographs to form aerodynamic noise sources. Slide plates, pantograph heads, balance rods, insulators, bottom frames, and push rods are the main aerodynamic noise source of pantographs. Radiated energies of pantographs are mainly in mid-frequency and high-frequency bands. In high-frequency bands, the far-field aerodynamic noise of pantographs is mainly contributed by the pantograph head. Single-frequency noises are in the far-field aerodynamic noise of pantographs, where main frequencies are 293 Hz, 586 Hz, 880 Hz, and 1173 Hz. The farther the observed point is from the noise source, the faster the sound pressure attenuation will be. When the distance of two adjacent observed points is increased by double, the attenuation amplitude of sound pressure levels for pantographs is around 6.6 dB.
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Quan, Vu Hai. "RESEARCH AND OPTIMIZATION OF SPORT UTILITY VEHICLE AERODYNAMIC DESIGN." Applied Engineering Letters : Journal of Engineering and Applied Sciences 9, no. 2 (2024): 105–15. http://dx.doi.org/10.46793/aeletters.2024.9.2.5.

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Drag and lift are two important parameters to evaluate a vehicle’s aerodynamic performance. Aerodynamic resistance (drag force Fd) prevents the movement of the vehicle and has a value proportional to the square of the velocity. That is, when the speed increases twice, the aerodynamic drag will increase fourfold. This article presents a plan to design a sport utility vehicle model with improved aerodynamics by using Ansys Fluent software to analyze pressure distribution areas that affect aerodynamics and the body. Based on the results obtained, the areas of stress and maximum pressure concentration have been identified. From this, a plan to improve the vehicle’s exterior design has been proposed. After many iterations of the design and model optimization process, the aerodynamic drag coefficient CD was reduced by 3.06% compared to the original model. The revised design option is equipped with an airflow diffuser under the vehicle; the lifting resistance coefficient has been reduced from 0.0902 to 0.038, equivalent to 58.2%. The new proposed design of the model has reduced the vehicle’s frontal drag by 2.04%. The research results have determined the aerodynamic coefficients CD and CL of the model car. Based on the results received, it is possible to compare them with the manufacturer’s announced parameters and propose new design options that still ensure aesthetics.
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Metar, Manas. "Aerodynamic Analysis of Spoiler at Varying Speeds and Angles." International Journal for Research in Applied Science and Engineering Technology 9, no. 11 (November 30, 2021): 526–35. http://dx.doi.org/10.22214/ijraset.2021.38843.

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Abstract: Spoilers have been there in practice since years for the purpose of improving aerodynamics of a car. The pressure drag created at the end of the vehicle, referred to as wake region affects handling of the vehicle. This could be hazardous for the cars at high speeds. By adding a spoiler to the rear of the car reduces that pressure drag and the enhanced downforce helps in better traction. The paper presents aerodynamic analysis of a spoiler through Computational Fluid Dynamics analysis. The spoiler is designed using Onshape software and analyzed through SIMSCALE software. The simulation is carried out by changing angles of attack and velocities. The simulation results of downforce and drag are compared on the basis of analytical method. Keywords: Designing a spoiler, Design and analysis of spoiler, Aerodynamics of spoiler, Aerodynamic analysis of spoiler, Computational fluid dynamics, CFD analysis, CFD analysis of spoiler, Spoiler at variable angles, Types of spoilers, Analytical aerodynamic analysis.
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Ben Mosbah, A., R. M. Botez, and T. M. Dao. "New methodology combining neural network and extended great deluge algorithms for the ATR-42 wing aerodynamics analysis." Aeronautical Journal 120, no. 1229 (May 27, 2016): 1049–80. http://dx.doi.org/10.1017/aer.2016.46.

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ABSTRACTThe fast determination of aerodynamic parameters such as pressure distributions, lift, drag and moment coefficients from the known airflow conditions (angles of attack, Mach and Reynolds numbers) in real time is still not easily achievable by numerical analysis methods in aerodynamics and aeroelasticity. A flight parameters control system is proposed to solve this problem. This control system is based on new optimisation methodologies using Neural Networks (NNs) and Extended Great Deluge (EGD) algorithms. Validation of these new methodologies is realised by experimental tests using a wing model installed in a wind tunnel and three different transducer systems (a FlowKinetics transducer, an AEROLAB PTA transducer and multitube manometer tubes) to determine the pressure distribution. For lift, drag and moment coefficients, the results of our approach are compared to the XFoil aerodynamics software and the experimental results for different angles of attack and Mach numbers. The main purpose of this new proposed control system is to improve, in this paper, wing aerodynamic performance, and in future to apply it to improve aircraft aerodynamic performance.
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Zhang, Ying Chao, Zhe Zhang, Shuang Hu Luo, and Jian Hua Tian. "Aerodynamic Numerical Simulation in the Process of Car Styling." Applied Mechanics and Materials 16-19 (October 2009): 862–65. http://dx.doi.org/10.4028/www.scientific.net/amm.16-19.862.

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With the development of automotive industry of China, more and more new cars are brought out. Then more and more stylists and engineers will take part in car styling to design new car. In the process of car styling, Car aerodynamics is important to its performance. Especially for more excellent handling and stability performance, more aerodynamic analysis and optimization should been done. At first it was introduced that the process of car styling in this paper. The functions of aerodynamics in the process were indicated. Secondly some ways of aerodynamic analysis were put forward. The first one is wind tunnel test and the second one called virtual wind tunnel test. The virtual wind tunnel test is one of the best modern ways of aerodynamic design which apply in the fields of aerodynamic research widely. It was based on computational fluid dynamics. The details of the virtual wind tunnel test simulation were narrated in this paper. Applying the virtual wind tunnel test aerodynamic drag coefficient, velocity contour and pressure distribution were got. Some advices to reduce aerodynamic drag of the design car were put forward. In one word, it is one simple, effective, convenient and fast way for aerodynamic design in car styling process using virtual wind tunnel test.
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Dissertations / Theses on the topic "Aerodynamic pressure"

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Gonçalves, Duarte. "Aerodynamic study of atmospheric-pressure plasma jets." Electronic Thesis or Diss., université Paris-Saclay, 2024. http://www.theses.fr/2024UPASP101.

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Les jets de plasma à pression atmosphérique (JPPAs) étendent le plasma au-delà des parois d'un réacteur. Ces sources de plasma produisent et délivrent des espèces réactives à des matériaux sensibles. En conséquence, les JPPAs ont de nombreuses applications en biologie, médecine, analyse chimique et traitement des matériaux. Les JPPAs sont produits par le passage répétitif d'ondes d'ionisation (OI), guidées en aval par l'écoulement. À leur tour, les OI perturbent l'écoulement à chaque passage. L'étude de l'aérodynamique des JPPAs offre un chemin pour comprendre le couplage plasma-écoulement. Dans ce travail, nous étudions un JPPA d'argon coaxial, avec du gaz de blindage de N₂ et O₂, à travers des expérimentations et de la modélisation. Les expériences montrent deux décharges produites par une impulsion de tension appliquée : une à la montée et une autre à la descente. Chaque décharge produit des métastables d'argon, dont la densité peut être modulée en variant la fraction d'O₂ dans le gaz de blindage. Les températures rotationnelles et vibrationnelles augmentent pendant les décharges, indiquant des transferts d'énergie des électrons aux espèces lourdes. Nous visualisons le jet par imagerie de Schlieren, y compris comment une seule décharge crée des perturbations d'écoulement. En parallèle, nous avons adapté le code SPARK-CFD, initialement écrit pour les plasmas de rentrée, pour simuler les JPPAs sur plusieurs impulsions. Les simulations non réactives montrent comment la géométrie du réacteur affecte la vitesse et la composition chimique dans les jets simples et coaxiaux. Les simulations de JPPA montrent un chauffage des électrons et une excitation et ionisation subséquentes des atomes et molécules. Ce transfert d'énergie provoque une augmentation rapide de la température/pression, modifiant le champ de vitesse du jet. Ces effets s'accumulent sur plusieurs impulsions, changeant les profils spatiaux et temporels du jet et des espèces réactives. Finalement, la version adaptée de SPARK-CFD sera publiée en open-source, fournissant un code pour des simulations des plasmas subsoniques et hypersoniques<br>Cold atmospheric pressure plasma jets (APPJs) extend plasma beyond the walls of a reactor. These versatile plasma sources produce and deliver reactive species to sensitive materials. Accordingly, APPJs have many applications in biology, medicine, chemical analysis, and material processing. APPJs are produced by the repetitive passage of ionization waves (IWs), which are guided downstream by the flow. In turn, IWs perturb the flow at each passage. Studying the aerodynamics of APPJs provides a path to understanding the plasma-flow coupling. In this work, we study a co-axial argon APPJ with varying N₂ and O₂ shielding gas mixtures through experimental approaches and computational modelling. Experiments show two discharges produced by a square pulse of applied voltage: one at the rising and another at the falling edge. Each discharge produces argon metastables, whose maximum density can be modulated by varying the fraction of O₂ in the shielding gas. Rotational and vibrational temperatures increase during the discharges, indicating fast energy transfers from electrons to heavy species. We visualize the jet through Schlieren imaging, including how a single discharge creates coherent flow perturbations. In parallel, we adapted the SPARK code, initially designed for reentry plasmas, to simulate APPJs pulse-by-pulse and across multiple pulses. Non-reactive simulations show how the reactor's geometry affects the velocity and chemical composition in single and co-axial jet flows. In agreement with experiments, plasma jet simulations show electron heating and subsequent excitation and ionization of atoms and molecules. This energy transfer to heavy species causes a fast temperature/pressure increase, altering the velocity field of the jet. These effects accumulate over multiple pulses, changing the jet and reactive species' spatial and temporal profiles. Finally, the adapted version of SPARK will be released as open-source, providing a code for temporally accurate simulations of plasmas, including flows in subsonic and hypersonic conditions<br>Os jatos de plasma à pressão atmosférica (JPPAs) estendem um plasma além das paredes do reator. Estes plasmas são versáteis, produzindo e transportando espécies reativas que podem ser aplicadas em materiais sensíveis. São assim usados por em várias indústrias como a biológica, médica, de análise química e de processamento de materiais. Os JPPAs são produzidos pela passagem repetitiva de ondas de ionização (OIs), que são guiadas a jusante pelo escoamento. sendo este também perturbado pelo próprio plasma. Estudar a aerodinâmica dos JPPAs fornece um caminho para entender o acoplamento plasma-escoamento. Nesta tese, estudámos um JPPA coaxial de árgon, blindado por uma mistura de N₂ e O₂, através de experiências e modelização numérica. Experimentalmente observam-se duas descargas elétricas durante cada pulso de tensão aplicada: uma na subida e outra na descida do pulso. Cada descarga produz metaestáveis de árgon, cuja densidade pode ser modulada variando a fração de O₂ no gás de blindagem. Temperaturas rotacionais e vibracionais aumentam durante as descargas, indicando uma transferência rápida de energia entre eletrões e espécies pesadas. Imagiologia de Schlieren permite-nos ver o escoamento, incluindo como uma única descarga cria perturbações coerentes no mesmo. Paralelamente, adaptamos o código SPARK, inicialmente escrito para plasmas de reentrada atmosférica, para simular APPJs ao longo de múltiplos pulsos. Simulações mostram como a geometria do reator afeta a velocidade e a composição química do escoamento em jatos simples e coaxiais. Com plasma, nota-se o aquecimento dos eletrões e subsequente excitação e ionização de átomos e moléculas. Esta transferência de energia para espécies pesadas causa um aumento de temperatura e pressão, alterando o campo de velocidade do jato. Estes efeitos acumulam-se ao longo de múltiplos pulsos, mudando o perfil espaciotemporal do jato e das espécies reativas. Por fim, a versão adaptada do SPARK-CFD será lançada em código aberto, fornecendo uma ferramenta para simulações temporalmente precisas de plasmas subsónicos e hipersónicos
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BIGANZOLI, ILARIA. "Characterization of atmospheric pressure plasmas for aerodynamic applications." Doctoral thesis, Università degli Studi di Milano-Bicocca, 2014. http://hdl.handle.net/10281/53249.

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The use of plasmas in aerodynamics has become a recent topic of interest. In particular, over the last ten years, plasma actuation has received much attention as a promising active method for airflow control. Flow control consists of manipulating the properties of a generic moving fluid with the aim of achieving a desired change, but flow dynamics in proximity of a solid object is usually considered, being a consistent and significant issue in many engineering applications, such as engine, automobile or airplane design. Plasma control of airflows along surfaces has been the subject of several experimental studies whose aim was to reduce turbulence, to decrease drag, to enhance airfoil lift or to prevent flow detachment. The fast temporal response and the absence of moving parts are the most promising features from which plasma actuators could benefit. Different types of plasma sources are currently studied as good candidates for plasma actuation, but Dielectric Barrier Discharges (DBDs) are usually preferred, being characterized by the presence of an insulating barrier between the electrodes. This allows the generation of a non-thermal plasma at atmospheric pressure and prevents the discharge from collapsing into an arc. Surface Dielectric Barrier Discharges (SDBDs) are particularly suitable for these kinds of applications, since plasma is created by ionizing a thin portion of air nearby the surface of the dielectric barrier and this can effectively influence the local properties of the boundary layer associated to an external flow. This thesis deals with SDBDs in an asymmetric configuration where one electrode is glued into an insulating material and to other one is exposed to air, so that plasma is created in correspondence of just one side of the dielectric barrier. The buried electrode is connected to the ground, whereas a sinusoidal high-voltage is applied to the exposed one. It has been noticed that, when these discharges are operated in quiescent air, an airflow of several metres per second is observed above the dielectric sheet and near the plasma region. This is usually called ionic wind because the main mechanism responsible for its generation is believed to be momentum transfer from the ions drifting in the discharge electric field to the surrounding fluid, by particle-particle collisions. When the electric field imposed by the voltage difference between the electrodes is sufficiently high, plasma is created and electrical charges are transported through the gap and accumulated on the insulating surfaces. This charge accumulation generates an electric field that locally weakens the external one. When the total electric field falls below the threshold necessary for plasma ignition, the discharge extinguishes. If the voltage imposed to the fed electrode is increased, the discharge can be locally initiated again, and that is the reason why a sinusoidal high-voltage supply is adopted instead of a continuous one. Consequently, the presence of the insulating barrier usually leads to a regime where charge is mainly transported in sub-millimetre regions consisting of current filaments with temporal duration limited to a few tens of nanoseconds. These plasma microdischarges are concentrated into two phase intervals of the sinusoidal voltage supply, when the modulus of the applied voltage difference is high enough and is increasing in time. These two phases of plasma activity are often called Backward Stroke (BD) and Forward Stroke (FD), depending if the high-voltage signal is rising from its minimum to its maximum or decreasing from its maximum to its minimum. This thesis is motivated by the fact new studies focusing on plasma properties and dynamics are required in order to get better and better aerodynamic results, to understand which parameters mainly affect the actuator performances and to validate numerical models trying to forecast the aerodynamic effects induced by the discharge. This has brought to a scientific collaboration between the Centre of Excellence PlasmaPrometeo of University of Milano-Bicocca and the Aerodynamics and Wind Tunnel Department of the aerospace company Alenia Aermacchi. During these years I have studied the properties of these discharges by means of electrical and optical diagnostics (mainly Rogowski coils, capacitive probes, a photomultiplier tube and a thermal camera). With some of them a temporal resolution high enough for studying several characteristics of plasma microdischarges has been achieved. This is important because these strokes manifest as series of current and light pulses, lasting tens of nanoseconds and a few nanoseconds respectively. I have first of all carried out a detailed investigation of the properties of these events and of their evolution in space and time in the course of the FD and BD. It has been pointed out that there are several analogies between the BD and FD, but that not all plasma properties are identical for the two semi-cycles, because of the asymmetrical configuration adopted. These investigations let think that light and current signals give insights about different microdischarge properties. Light is presumably ascribable to electrons that excite nitrogen immediately after the passage of the ionizing wave that initiates the microdischarge. In contrast, the current signal is due to the movement of charges into the plasma channel and thus reflects the microdischarge temporal evolution, rather than its formation. In the following experiments I have thus focused mainly on the electrical properties of plasma microdicharges, with the aim of better understanding which plasma characteristics are responsible for the ionic wind generation and properties. Several SDBDs with different geometrical configurations and operating parameters have been considered. It has been found that both the discharge and ionic wind characteristics are mainly affected by the dielectric thickness, whereas other properties of the SDBD are less decisive. These studies are of practical interest because optimizations of SDBD characteristics are still needed for adopting these discharges as plasma actuators for active flow control. In particular, it has been found that at first the speed of the induced wind increases quite linearly with the voltage amplitude, but then this velocity and thus the aerodynamic effects induced by the discharge tend to saturate. This is particularly evident when thin panels are adopted as dielectric barriers. I thus focused on this topic and I found that an asymmetry in the total charge transported by plasma microdischarges during the backward and forward strokes is favourable for obtaining a ionic wind with a greater velocity, and that the velocity saturation at the highest voltages is associated to a change in discharge regime, which is visible first of all because a pattern of plasma filaments appears superimposed to the more homogeneous plasma. I have thus characterized how this regime transition affects the dynamics of the backward and forward strokes. Three groups of microdischarges have been identified, depending on their temporal duration, and results let think that they don't contribute equally to the electric wind generation. These studies pave the way to a better understanding of the discharge peculiarities and ionic wind formation, with the aim of understanding if an intrinsic limit exists in plasma actuator potentialities or if new optimization strategies are possible. Eventually, I proposed to implement the Background Oriented Schlieren (BOS) technique for the visualization and characterization of the airflow induced by the discharge. The potentialities of this technique have been evaluated in relation to the specifics of the available scientific equipment. The technique has then been proved to be able to visualize density changes induced by plasma. A spatial characterization of the air near the discharge was made in stationary wall jet conditions as well as in the transient period following the discharge ignition when a starting vortex is generated.
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Bamberger, Konrad [Verfasser]. "Aerodynamic Optimization of Low-Pressure Axial Fans / Konrad Bamberger." a : Shaker, 2015. http://d-nb.info/1080762191/34.

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Holmberg, Eva. "Aerodynamic measurements of normal voice." Doctoral thesis, Stockholms universitet, Institutionen för lingvistik, 1993. http://urn.kb.se/resolve?urn=urn:nbn:se:su:diva-40215.

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Vocal fold vibration results from an alternating balance between subglottal air pressure that drives the vocal folds apart and muscular, elastic, and restoring forces that draw them together. The aim of the present thesis is to present quantitative data of normal vocal function using a noninvasive method. Measurements are made on the inverse filtered airflow waveform, of estimated average trans glottal pressure and glottal airflow, and of sound pressure for productions of syllable sequences. Statistical results are used to infer mechanisms that underlie differences across ( 1 ) normal, loud, and soft voice, (2) normal, high, and low pitch, and (3) between female and male voices. Interspeaker variation in group data and intra speaker variation across repeated recordings is also investigated. The results showed no significant female-male differences in pressure, suggesting that differences in other measures were not primarily due to differences in the respiratory systems . Most glottal waveforms showed a DC flow offset, suggesting an air leakage through a posterior glottal opening. Results suggested (indirectly) that the males in comparison with the females had significantly higher vocal fold closing velocities (maximum flow declination rate), larger vocal fold oscillations (AC flow), and relatively longer closed portions of the cycle (open quotient) in normal and loud voice. In soft voice, female and male waveforms were more alike. In comparison with normal voice, both females and males produced loud voice with significantly higher values of pressure, vocal fold closing velocity, and AC flow. Soft voice was produced with significantly lower values of these measures and increased DC flow. Correlation analyses indicated that several of the airflow measures were more directly related to vocal intensity than to pitch. Interspeaker variation was large, emphasizing the importance of large subject groups to capture normal variation. Intraspeaker variation across recording sessions was less than 2 standard deviations of the group means. The results should contribute to the understanding of normal voice function, and should be useful as norms in studies of voices disorders as well.<br>Härtill 5 uppsatser.För att köpa boken skicka en beställning till exp@ling.su.se/ To order the book send an e-mail to exp@ling.su.se
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Grodek, Kristen Ashley. "The Effect of Sound Pressure Level Variation on Aerodynamic Measures." Miami University / OhioLINK, 2009. http://rave.ohiolink.edu/etdc/view?acc_num=miami1239321162.

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Rossetti, Alessandro <1977&gt. "Design and development of new pressure sensors for aerodynamic applications." Doctoral thesis, Alma Mater Studiorum - Università di Bologna, 2008. http://amsdottorato.unibo.it/787/1/Tesi_Rossetti_Alessandro.pdf.

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This artwork reports on two different projects that were carried out during the three years of Doctor of the Philosophy course. In the first years a project regarding Capacitive Pressure Sensors Array for Aerodynamic Applications was developed in the Applied Aerodynamic research team of the Second Faculty of Engineering, University of Bologna, Forlì, Italy, and in collaboration with the ARCES laboratories of the same university. Capacitive pressure sensors were designed and fabricated, investigating theoretically and experimentally the sensor’s mechanical and electrical behaviours by means of finite elements method simulations and by means of wind tunnel tests. During the design phase, the sensor figures of merit are considered and evaluated for specific aerodynamic applications. The aim of this work is the production of low cost MEMS-alternative devices suitable for a sensor network to be implemented in air data system. The last two year was dedicated to a project regarding Wireless Pressure Sensor Network for Nautical Applications. Aim of the developed sensor network is to sense the weak pressure field acting on the sail plan of a full batten sail by means of instrumented battens, providing a real time differential pressure map over the entire sail surface. The wireless sensor network and the sensing unit were designed, fabricated and tested in the faculty laboratories. A static non-linear coupled mechanical-electrostatic simulation, has been developed to predict the pressure versus capacitance static characteristic suitable for the transduction process and to tune the geometry of the transducer to reach the required resolution, sensitivity and time response in the appropriate full scale pressure input A time dependent viscoelastic error model has been inferred and developed by means of experimental data in order to model, predict and reduce the inaccuracy bound due to the viscolelastic phenomena affecting the Mylar® polyester film used for the sensor diaphragm. The development of the two above mentioned subjects are strictly related but presently separately in this artwork.
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Rossetti, Alessandro <1977&gt. "Design and development of new pressure sensors for aerodynamic applications." Doctoral thesis, Alma Mater Studiorum - Università di Bologna, 2008. http://amsdottorato.unibo.it/787/.

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This artwork reports on two different projects that were carried out during the three years of Doctor of the Philosophy course. In the first years a project regarding Capacitive Pressure Sensors Array for Aerodynamic Applications was developed in the Applied Aerodynamic research team of the Second Faculty of Engineering, University of Bologna, Forlì, Italy, and in collaboration with the ARCES laboratories of the same university. Capacitive pressure sensors were designed and fabricated, investigating theoretically and experimentally the sensor’s mechanical and electrical behaviours by means of finite elements method simulations and by means of wind tunnel tests. During the design phase, the sensor figures of merit are considered and evaluated for specific aerodynamic applications. The aim of this work is the production of low cost MEMS-alternative devices suitable for a sensor network to be implemented in air data system. The last two year was dedicated to a project regarding Wireless Pressure Sensor Network for Nautical Applications. Aim of the developed sensor network is to sense the weak pressure field acting on the sail plan of a full batten sail by means of instrumented battens, providing a real time differential pressure map over the entire sail surface. The wireless sensor network and the sensing unit were designed, fabricated and tested in the faculty laboratories. A static non-linear coupled mechanical-electrostatic simulation, has been developed to predict the pressure versus capacitance static characteristic suitable for the transduction process and to tune the geometry of the transducer to reach the required resolution, sensitivity and time response in the appropriate full scale pressure input A time dependent viscoelastic error model has been inferred and developed by means of experimental data in order to model, predict and reduce the inaccuracy bound due to the viscolelastic phenomena affecting the Mylar® polyester film used for the sensor diaphragm. The development of the two above mentioned subjects are strictly related but presently separately in this artwork.
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Garrison, Courtney Rollins. "Repeatability of Aerodynamic Measurements of Voice." Miami University / OhioLINK, 2009. http://rave.ohiolink.edu/etdc/view?acc_num=miami1239309229.

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Yoon, Sungho. "Advanced aerodynamic design of the intermediate pressure turbine for aero-engines." Thesis, University of Cambridge, 2010. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.608551.

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Wang, Yifei. "Experimental Study of Wheel-Vehicle Aerodynamic Interactions." Thesis, Chasseneuil-du-Poitou, Ecole nationale supérieure de mécanique et d'aérotechnique, 2019. http://www.theses.fr/2019ESMA0002/document.

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Sur une maquette à l’échelle 2/5ième équipée d’un diffuseur et de pneus Michelin. La géométrie du véhicule, basée sur le modèle ASMO, a été modifiée précédemment à ce travail afin d’obtenir un angle d’attaque de l’écoulement sur les roues avant et un équilibre du sillage réaliste en présence de quatre roues tournantes. Cette configuration a servi de référence dans le cadre de cette étude.Il a été mis en évidence que la configuration de base avec un sillage équilibré peut facilement être modifiée d’un point de vue aérodynamique en changeant l’état des roues (en rotation ou pas) et le type de pneumatique, en particulier sur l’essieu arrière. Cela provient d’un effet global et d’une sensibilité importante de l’équilibre du sillage aux changements de débit au soubassement. A contrario, lorsque le sillage du véhicule se trouve déséquilibré, il devient plus robuste par rapport à des perturbations de soubassement comme un changement d’état des roues ou une modification des pneumatiques. Si l’on supprime les quatre roues ou uniquement les deux roues avant, le débit de quantité de mouvement au soubassement est grandement augmenté. Par contre, si l’on supprime le diffuseur (changement important de la géométrie du véhicule), celui-ci s’en trouve nettement réduit. Dans ces deux configurations, le sillage est très fortement déséquilibré vers le sol et devient indépendant aux modifications apportées sur les roues.Il a également été mis en évidence un effet plus local du sillage des roues sur la portance et la traînée du véhicule.En effet, la zone de dépression dans le sillage des roues avant a un effet sur la portance alors que le sillage des roues arrière pilote en partie la pression au culot et donc la traînée. Il a ainsi été observé une augmentation importante de la traînée du véhicule lorsque le sillage des roues arrière, non fermé, venait en interaction directe avec le sillage du véhicule<br>The thesis aims to provide a better understanding of the wheel-vehicle interaction, via experimental investigations on a 2/5-th scale vehicle with an underbody diffuser and 2/5-th scale wheels equipped with Michelin tires. The vehicle geometry, based on ASMO model, was modified prior to the PhD work, in order to achieve a reasonable front wheel yaw angle, and a realistic wake balance with four rotating wheels. It is the baseline configuration in the scope of this work.The findings demonstrate that the well-balanced wake of the baseline configuration can be easily modified by different wheel states or tire modifications, especially at the rear axle. This results from a global effect of the underbody momentum modifications, i.e. a high wake sensitivity to the underbody flow. On the contrary, when the vehicle mean wake develops into a non-balanced topology, it is more robust towards underbody perturbations such as different wheel states or tire modifications. By eliminating four wheels or front wheels, the underbody momentum flux is vastly increased; by eliminating the underbody diffuser, which is a vehicle geometry modification, the underbody momentum flux is significantly reduced. In these two circumstances, one can observea robust downwash from the roof, independent of the wheel states or tire modifications. Besides, there is a more local effect of the wheels near wakes on the aerodynamic lift and drag of the vehicle. Low pressure regions in the underbody downstream the front wheels have an effect on vehicle lift. The rear wheels impose pressure conditions on the vehicle base, influencing the vehicle drag. Particularly, the merging of nonclosed mean wakes of the rear wheels with the vehicle wake can give rise to strong penalty in vehicle drag
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Books on the topic "Aerodynamic pressure"

1

K, Notestine Kristopher, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. Aerodynamic pressure and heating-rate distributions in tile gaps around chine regions with pressure gradients at a Mach number of 6.6. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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Moshasrov, V. Luminescent pressure sensors in aerodynamic experiments. Zhukovsky, Russia : Central Aerohydrodynamic Institute (TsAGI): CWA 22 Corporation, 1998.

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H, Ricketts Rodney, Hess R. W, and Langley Research Center, eds. Recent transonic unsteady pressure measurements at the NASA Langley Research Center. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1985.

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Schuster, D. M. Aerodynamic measurements on a large splitter plate for the Langley Transonic Dynamics Tunnel. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 2001.

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E, Mineck Raymond, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Aerodynamic characteristics and pressure distributions for an executive-jet baseline airfoil section. [Washington, DC]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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Nemec, Marian. Aerodynamic computations using the convective upstream split pressure scheme with local preconditioning. [Toronto]: Dept. of Aerospace Science and Engineering, University of Toronto, 1998.

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Nemec, Marian. Aerodynamic computations using the convective upstream split pressure scheme with local preconditioning. Ottawa: National Library of Canada, 1998.

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Labrujere, Th E. Correction for wall interference in a solid-wall wind tunnel using sparse measured boundary conditions. Amsterdam: National Aerospace Laboratory, 1989.

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United States. National Aeronautics and Space Administration., ed. IPAC--Inlet Performance Analysis Code. [Washington, DC: National Aeronautics and Space Administration, 1997.

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United States. National Aeronautics and Space Administration., ed. IPAC--Inlet Performance Analysis Code. [Washington, DC: National Aeronautics and Space Administration, 1997.

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Book chapters on the topic "Aerodynamic pressure"

1

Decher, Reiner. "The Compressor: Gas Turbine Engine Keystone." In The Vortex and The Jet, 109–19. Singapore: Springer Singapore, 2022. http://dx.doi.org/10.1007/978-981-16-8028-1_10.

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AbstractAll engines involve the raising of pressure in the engine’s medium, be it liquid compression of water, piston-cylinder compression of air or compression by aerodynamic forces. The last is the hardest because it is required to be efficient and stable. An aerodynamic air compressor works by slowing velocities to raise pressure. The airfoil has a difficult time doing this reliably and well and so does the compressor. When it does, it allows for amazing performance of the engine in terms of power and efficiency.
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Paluch, B. "Light transmission control technique and correlation with pressure loss characteristics of perforated panels for Hybrid Laminar Flow Applications." In Aerodynamic Drag Reduction Technologies, 71–78. Berlin, Heidelberg: Springer Berlin Heidelberg, 2001. http://dx.doi.org/10.1007/978-3-540-45359-8_9.

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Ellis, J. E., S. A. Walsh, and D. I. A. Poll. "Assessment of the eN Method as a Transition Prediction Tool for Zero Pressure Gradient Flows with and without Boundary Layer Suction." In Aerodynamic Drag Reduction Technologies, 323–32. Berlin, Heidelberg: Springer Berlin Heidelberg, 2001. http://dx.doi.org/10.1007/978-3-540-45359-8_34.

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Hölscher, N., and H. J. Niemann. "Non-Parametric Identification of a Multiple Aerodynamic Pressure Admittance." In Notes on Numerical Fluid Mechanics (NNFM), 225–32. Wiesbaden: Vieweg+Teubner Verlag, 1993. http://dx.doi.org/10.1007/978-3-663-13986-7_30.

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Liu, Kaihe, Haitao Chang, and Yang Li. "Some Thoughts About the Aerodynamic Pressure Center of Automobile." In Lecture Notes in Electrical Engineering, 675–86. Singapore: Springer Nature Singapore, 2024. http://dx.doi.org/10.1007/978-981-97-0252-7_48.

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Huang, Thomas T., and Ming-Shun Chang. "Computation of Velocity and Pressure Variation Across Axisymmetric Thick Turbulent Stern Flows." In Numerical and Physical Aspects of Aerodynamic Flows III, 341–59. New York, NY: Springer New York, 1986. http://dx.doi.org/10.1007/978-1-4612-4926-9_19.

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Zharkova, G. M., A. I. Maksimov, A. A. Pavlov, and V. M. Khachaturyan. "Pressure Visualization on Aerodynamic Surface by the Method of Luminescent Coating." In Flow Visualization VI, 617–22. Berlin, Heidelberg: Springer Berlin Heidelberg, 1992. http://dx.doi.org/10.1007/978-3-642-84824-7_109.

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Usherwood, James R. "The aerodynamic forces and pressure distribution of a revolving pigeon wing." In Animal Locomotion, 429–41. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010. http://dx.doi.org/10.1007/978-3-642-11633-9_33.

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Wu, Meng-ling, Yang-yong Zhu, Chun Tian, and Wei-wei Fei. "Influence of Aerodynamic Braking on the Pressure Wave of a Crossing High-Speed Train." In China's High-Speed Rail Technology, 133–42. Singapore: Springer Singapore, 2017. http://dx.doi.org/10.1007/978-981-10-5610-9_8.

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Kulkarni, Nitish, D. Harish, R. D. Bharathan, Sharad Kapil, S. V. Ramana Murthy, R. Senthil Kumaran, and D. Kishore Prasad. "Numerical Investigation of Aerodynamic Performance Parameters in Linear Blade Cascade for High-pressure Turbine." In Proceedings of the National Aerospace Propulsion Conference, 145–55. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-19-2378-4_9.

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Conference papers on the topic "Aerodynamic pressure"

1

CARVER, D., W. WARD, and M. BYERS. "Continuous sweep pressure prediction technique." In 14th Aerodynamic Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-767.

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Birkenstock, David. "Increased Fuel Economy From Powered Aerodynamics and Aerodynamic Pressure Thrust." In 18th AIAA Lighter-Than-Air Systems Technology Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-2864.

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STAINBACK, P., R. MCGHEE, W. BEASLEY, and H. MORGAN, JR. "The Langley Research Center's Low-Turbulence Pressure Tunnel." In 14th Aerodynamic Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-762.

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MORRIS, M., J. DONOVAN, J. KEGELMAN, S. SCHWAB, R. LEVY, and R. CRITES. "Aerodynamic applications of pressure-sensitive paint." In 30th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1992. http://dx.doi.org/10.2514/6.1992-264.

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FUNG, Y. T., G. SETTLES, and A. RAY. "Microprocessor control of high-speed wind tunnel stagnation pressure." In 15th Aerodynamic Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-2062.

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SMELTZER, D., and A. LEVIN. "Evaluation of an electronic scanner of pressure (ESOP) module." In 14th Aerodynamic Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-771.

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Larsen, Allan. "Horizontal Aerodynamic Derivatives in Bridge Flutter Analysis." In ASME 2014 Pressure Vessels and Piping Conference. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/pvp2014-28251.

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Inclusion of a horizontal degree of freedom along with the vertical and twisting degrees of freedom has been an active area of research in bridge flutter predictions for the past three decades. While much work has been published on theoretical aspects, limited experience as to the importance of the horizontal degree of freedom is available in the literature. Three cases of actual long span bridge designs are examined with respect to the critical wind speed for onset of classical flutter. For the tree cases examined inclusion of the horizontal modes of motion had almost negligible influence on the flutter wind speed.
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CHUNG, KUNG-MING, and FRANK LU. "Shock-tube calibration of a fast-response pressure transducer." In 16th Aerodynamic Ground Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-1399.

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Chang, Y. B., and P. M. Moretti. "Aerodynamic Characteristics of Pressure-Pad Air Bars." In ASME 1997 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 1997. http://dx.doi.org/10.1115/imece1997-0091.

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Abstract Air flotation ovens are widely used for non-contact support and drying of coated papers and plastic films (generically called webs). The main components in air flotation ovens are air bars which have slot nozzles through which hot air jets are ejected. Problems in air flotation drying techniques include sideward motion of the web, web flutter, and contact between the web and air bars. The key to analyzing these problems is to determine the aerodynamic forces on the web. This paper discusses the aerodynamic forces generated by pressure-pad type air bars, each of which has two slot nozzles. Ground-effect theories, which were originally developed for the design of hovercraft, are applied to air bars. Aerodynamic forces for typical air bars were measured for different values of flotation height, and the results were compared with the theories. It is shown that ground effect theories can be applied to pressure-pad type air bars if we properly define the equivalent values of the ground effect variables, which include nozzle thickness (thickness of air jet), flotation height, angle of ejection of air jet, and total pressure of the air jet at the nozzle.
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Zolotarev, Igor, Václav Vlček, and Jan Kozánek. "Unsteady Aerodynamic Forces Measured on a Fluttering Profile." In ASME 2014 Pressure Vessels and Piping Conference. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/pvp2014-28567.

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The study presents evaluation of optical measurements of the air flow field near the fluttering profile NACA0015 with two-degrees of freedom, Mach number of the flutter occurrence were M=0.21 and M=0.45. Aerodynamic forces (drag and lift components) were evaluated independently on the upper and lower surfaces of the profile. Using the mentioned decomposition, the new information about mechanism of flutter properties was obtained. The forces on the upper and lower surfaces are phase shifted and are partially eliminated as a result of the circulation around the profile. The cycle changes of these forces cause the permanent energy contribution from the airflow to the vibrating system.
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Reports on the topic "Aerodynamic pressure"

1

Aerodynamic Development of the GAC ENO.146 Concept. SAE International, September 2021. http://dx.doi.org/10.4271/2021-01-5093.

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This paper describes the aerodynamic development process and features of the flow field of the GAC ENO.146, a concept vehicle shown in Guangzhou Auto Show 2019, which achieved a CD of 0.146. Key factors in the design process, including how design decisions are made and how the interactions occur between aerodynamicists and designers are explained in detail. The design language forms the next generation of BEVs. The aerodynamic development philosophy is guided by three principles: minimizing flow separation, maximizing rear pressure recovery, and controlling tire wake. This vehicle took full advantage of the unique 2-1-2-1 seating configuration that allowed a tapered tail design with a narrower rear track to further minimize the size of the rear recirculation zone, improving rear pressure recovery. In order to reduce induced drag, detailed studies on roofline and diffuser angles were conducted to develop the optimal combination, eliminating any loss of flow momentum. The diffuser design also served to eliminate flow separation caused by the rear wheels. In addition to that, active aerodynamic devices were employed to reduce interaction between freestream and wheelhouse air. A comparison was also made between ENO.146 and Aion S, a GAC production EV to illustrate future development potentials. Through the development of ENO.146, the aerodynamic development process of ENO.146 serves as a template for future projects, providing expertise and best practices of aerodynamic development for both engineers and designers.
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