Relevant bibliographies by topics / Aerodynamic pressure

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers

Academic literature on the topic 'Aerodynamic pressure'

Author: Grafiati
Published: 4 June 2021
Last updated: 4 February 2022

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Journal articles on the topic "Aerodynamic pressure"

1

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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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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Mordasov, M. M., A. P. Savenkov, and K. E. Chechetov. "Aerodynamic measurement of surface pressure." Izmeritel`naya Tekhnika, no. 5 (2018): 50–55. http://dx.doi.org/10.32446/0368-1025it.2018-5-50-55.

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Kozmar, Hrvoje, and Boris Laschka. "Pressure tap cavity for unsteady aerodynamic pressure measurements." Measurement 132 (January 2019): 282–91. http://dx.doi.org/10.1016/j.measurement.2018.09.056.

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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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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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Musa, Mohamad Nor, Samion Syahrullail, and Fairuz Zainal Abidin. "Aerodynamic Analysis on Proton Preve by Experimental." Applied Mechanics and Materials 773-774 (July 2015): 575–79. http://dx.doi.org/10.4028/www.scientific.net/amm.773-774.575.

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The purpose of this study is to determine the coefficient drag, CD of the Proton PREVẾ by experimental method using Low Speed Wind Tunnel. All the relevant data are collected through the literature reviews from books and journals. First, the basic thing in aerodynamic is studied. There are two things are concern when studies aerodynamics. They were air flow and vehicle shape which we regard as aerodynamics factor that determine aerodynamic of the vehicle. Fundamental of air flow and vehicle shape is reviewed includes the relationship between air speed with pressure, boundary layer, Reynolds number, drag, lift drag and shape optimization. Wind tunnel is also studied before the experiment. Five selected speed were been tasted during the experiment to determine the CD value.
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Schreck, S., and M. Robinson. "Boundary Layer State and Flow Field Structure Underlying Rotational Augmentation of Blade Aerodynamic Response." Journal of Solar Energy Engineering 125, no. 4 (November 1, 2003): 448–56. http://dx.doi.org/10.1115/1.1624087.

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Blade rotation routinely and significantly augments aerodynamic forces during zero yaw horizontal axis wind turbine (HAWT) operation. To better understand the flow physics underlying this phenomenon, time dependent blade surface pressure data were acquired from the National Renewable Energy Laboratory (NREL). Unsteady Aerodynamics Experiment (UAE), a full-scale HAWT tested in the NASA Ames 80-by-120-foot wind tunnel. Time records of surface pressures and normal force were processed to obtain means and standard deviations. Surface pressure means and standard deviations were analyzed to identify boundary layer separation and shear layer impingement locations. Separation and impingement kinematics were then correlated with normal force behavior. Results showed that rotational augmentation was linked to specific separation and impingement behaviors, and to associated three-dimensionality in surface pressure distributions.
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Sun, Xiao-Ying, Tian-E. Li, Guo-Chang Lin, and Yue Wu. "A study on the aerodynamic characteristics of a stratospheric airship in its entire flight envelope." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, no. 5 (August 2, 2017): 902–21. http://dx.doi.org/10.1177/0954410017723358.

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Aerodynamic characteristics of a stratospheric airship in its entire flight envelope, including take-off, ascending, cruising, descending, and landing, is an important part of its research topic. In this paper, experiments of wind pressure measurement on a 1/30-scale stratospheric airship model were carried out to obtain a better assessment of the aerodynamic characteristics during the cruising process. Based on the wind pressure distribution, the effects of pitch angle, yaw angle, and combined angles (pitch angle and yaw angle acted simultaneously) on the aerodynamics of the airship were analyzed. In addition, the contributions of different portions of the airship hull (namely head, middle, and tail) to the aerodynamic forces and moments were discussed. The experimental results imply that the tail portion is the main contributor to pressure drag force. The combined angles significantly increase aerodynamic forces and rolling moment, and the rolling moment produced by the middle portion accounts for the major proportion. Secondly, the computational fluid dynamics method was verified and employed to study the aerodynamic characteristics of the full-scale model in its entire flight envelope based on the decision of the wind environment parameters and attitude. As a main result, it can be concluded that, more attention should be paid to the airship when it is located in the troposphere and near the ground with an inclined take-off angle.
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Dissertations / Theses on the topic "Aerodynamic pressure"

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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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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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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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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.
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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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
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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Oram, C. E. "Aerodynamic surface pressure measurement in atmosphere and wind tunnel on a vertical axis wind turbine blade using pressure transducers." Thesis, Cranfield University, 1989. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.375937.

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Jöcker, Markus. "Numerical Investigation of the Aerodynamic Vibration Excitation of High-Pressure Turbine Rotors." Doctoral thesis, KTH, Energy Technology, 2002. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-3416.

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The design parameters axial gap and stator count of highpressure turbine stages are evaluated numerically towards theirinfluence on the unsteady aerodynamic excitation of rotorblades. Of particular interest is if and how unsteadyaerodynamic considerations in the design could reduce the riskofhigh cycle fatigue (HCF) failures of the turbine rotor.

A well-documented 2D/Q3D non-linear unsteady code (UNSFLO)is chosen to perform the stage flow analyses. The evaluatedresults are interpreted as aerodynamic excitation mechanisms onstream sheets neglecting 3D effects. Mesh studies andvalidations against measurements and 3D computations provideconfidence in the unsteady results. Three test cases areanalysed. First, a typical aero-engine high pressure turbinestage is studied at subsonic and transonic flow conditions,with four axial gaps (37% - 52% of cax,rotor) and two statorconfigurations (43 and 70 NGV). Operating conditions areaccording to the resonant conditions of the blades used inaccompanied experiments. Second, a subsonic high pressureturbine intended to drive the turbopump of a rocket engine isinvestigated. Four axial gap variations (10% - 29% ofcax,rotor) and three stator geometry variations are analysed toextend and generalise the findings made on the first study.Third, a transonic low pressure turbine rotor, known as theInternational Standard Configuration 11, has been modelled tocompute the unsteady flow due to blade vibration and comparedto available experimental data.

Excitation mechanisms due to shock, potential waves andwakes are described and related to the work found in the openliterature. The strength of shock excitation leads to increasedpressure excitation levels by a factor 2 to 3 compared tosubsonic cases. Potential excitations are of a typical wavetype in all cases, differences in the propagation direction ofthe waves and the wave reflection pattern in the rotor passagelead to modifications in the time and space resolved unsteadypressures on the blade surface. The significant influence ofoperating conditions, axial gap and stator size on the wavepropagation is discussed on chosen cases. The wake influence onthe rotorblade unsteady pressure is small in the presentevaluations, which is explicitly demonstrated on the turbopumpturbine by a parametric study of wake and potentialexcitations. A reduction in stator size (towards R≈1)reduces the potential excitation part so that wake andpotential excitation approach in their magnitude.

Potentials to reduce the risk of HCF excitation in transonicflow are the decrease of stator exit Mach number and themodification of temporal relations between shock and potentialexcitation events. A similar temporal tuning of wake excitationto shock excitation appears not efficient because of the smallwake excitation contribution. The increase of axial gap doesnot necessarily decrease the shock excitation strength neitherdoes the decrease of vane size because the shock excitation mayremain strong even behind a smaller stator. The evaluation ofthe aerodynamic excitation towards a HCF risk reduction shouldonly be done with regard to the excited mode shape, asdemonstrated with parametric studies of the mode shapeinfluence on excitability.

Keywords:Aeroelasticity, Aerodynamics, Stator-RotorInteraction, Excitation Mechanism, Unsteady Flow Computation,Forced Response, High Cycle Fatigue, Turbomachinery,Gas-Turbine, High-Pressure Turbine, Turbopump, CFD, Design

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Sharifian, Seyed Ahmad. "Fibre optic pressure transducers for disturbance measurements in transient aerodynamic research facilities." University of Southern Queensland, Faculty of Engineering and Surveying, 2003. http://eprints.usq.edu.au/archive/00001509/.

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Experiments in the study of transient aerodynamics typically require pressure measurements with a high spatial and temporal resolution. Existing commercial pressure transducers are expensive and they provide a spatial resolution only on the order of millimetres. The full bandwidth of commercial devices (which extends to around 200 kHz) can only be utilised by exposing the transducer to the flow environment with very little thermal or mechanical protection. If insufficient protection is provided, the expensive commercial devices are likely to be damaged. Inexpensive pressure sensors based on extrinsic Fabry-Perot fibre optic interferometry are capable of measurement with a high spatial and temporal resolution. Thermal protection or isolation for these sensors is still required, but they can be exposed directly to the flow if the sensors are disposable (low cost). Excessive thermal or mechanical protection is not required for these sensors because the damaging heat transfer and particle impacts that may occur in transient aerodynamic facilities generally occur after the useful test flow. In this dissertation, a variety of construction techniques for diaphragm-based Fabry-Perot fibre optic pressure sensors were investigated and the advantages and disadvantages of all techniques are compared. The results indicate that using a zirconia ferrule as the substrate, a liquid adhesive as the bonding layer, and a polished copper foil as the diaphragm provide the best results. It is demonstrated that a spatial resolution on the order of 0.1 mm and a bandwidth to more than 100 kHz can be achieved with such constructions. A variety of problems such as hysteresis, response irregularity, low visibility and sensor non-repeatability were observed. By using a thinner bonding layer, a larger bonding area, longer cavity length, increased calibration period, and applying load cycling to the diaphragm, the hysteresis was minimized. Sensor response irregularity was also minimized using a polished diaphragm. Visibility increased to about 90% using active control of the cavity length during the construction process. Non-repeatability was found to be a consequence of adhesive viscoelasticity and this effect was minimized using a thin layer of adhesive to bond the diaphragm to the substrate. Due to the effects of adhesive viscoelasticity, the pressure sensors indicate an error of up to 10% of mean value for the reflected shock pressure. This error could not be further reduced in the current sensors configuration. Some new configurations are proposed to decrease the effect of sensor non-repeatability. The effect of pretensioning the diaphragm was investigated analytically but the results do not indicate any considerable advantage for the levels of pretension likely to be achieved in practice. However, the results do indicate that pretension effects caused by an environmental temperature change can damage the sensor during storage. The effect of the initial diaphragm deflection on the sensor performance and temperature sensitivity was modelled and the results show that an initial diaphragm deflection can improve the sensor performance. The effect of the thermal isolation layer on the sensor performance was also investigated and the results show that for a shock tube diaphragm bursting pressure ratio up to 5.7, heat transfer does not contribute to sensor errors for the first millisecond after shock reflection. However, it was found that the use of a thin layer of low viscosity grease can protect the sensor for about 20 ms while only decreasing its natural frequency by typically 17%. The grease layer was also found to decrease the settling time of a low damping ratio sensor by 40%. The sensor was successfully employed to identify an acoustic disturbance in a shock tube.
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Books on the topic "Aerodynamic pressure"

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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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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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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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Emre, Ilgin Hüseyin, ed. Tall buildings: Structural systems and aerodynamic form. London: Routledge, Taylor & Francis Group, 2014.

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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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Wing, David J. Afterbody/nozzle pressure distributions of a twin-tail twin-enginer fighter with axisymmetric nozzles at Mach numbers from 0.6 to 1.2. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1995.

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Martin, Colin A. Surface pressure measurements on the wing of a wind tunnel model during steady rotation. Melbourne, Australia: Aeronautical Research Laboratory, 1991.

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Garry, Kevin P. A summary of the scale model wind tunnel measurements and full scale surface pressure tests on the Leyland T45 and DAF3300 vehicles used for the TRRL spray dispersion programme. Cranfield [U.K.]: College of Aeronautics, Cranfield Institute of Technology, 1987.

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Guerrera, Michael H. Laser anemometry and pressure measurements in the endwall region of an annular turbine cascade utilizing a pressurized aerodynamic window. Monterey, Calif: Naval Postgraduate School, 1996.

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Book chapters on the topic "Aerodynamic pressure"

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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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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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Ngouani, M. M. Siewe, Yong Kang Chen, R. Day, and O. David-West. "Low-Speed Aerodynamic Analysis Using Four Different Turbulent Models of Solver of a Wind Turbine Shroud." In Springer Proceedings in Energy, 149–54. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-63916-7_19.

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AbstractThis study presents the effect of four different turbulent models of solver on the aerodynamic analysis of a shroud at wind speed below 6 m/s. The converting shroud uses a combination of a cylindrical case and an inverted circular wing base which captures the wind from a 360° direction. The CFD models used are: the SST (Menter) k-ω model, the Reynolds Stress Transport (RST) model, the Improved Delay Detached Eddies Simulation model (IDDES) SST k-ω model and the Large Eddies Simulation Wall Adaptive model. It was found that all models have predicted a convergent surface pressure. The RST, the IDDES and the WALE LES are the only models which have well described regions of pressure gradient. They have all predicted a pressure difference between the planes (1–5) which shows a movement of the air from the lower plane 1 (inlet) to the higher plane 5 (outlet). The RST and IDDES have predicted better vorticities on the plane 1 (inlet). It was also found that the model RST, IDDES, and WALE LES have captured properly the area of turbulences across the internal region of the case. All models have predicted the point of flow separation. They have also revealed that the IDDES and the WALE LES can capture and model the wake eddies at different planes. Thus, they are the most appropriate for such simulation although demanding in computational power. The movement of air predicted by almost all models could be used to drive a turbine.
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Ragni, Daniele. "Pressure measurements." In Experimental Aerodynamics, 109–42. Boca Raton : CRC Press, 2017.: CRC Press, 2017. http://dx.doi.org/10.1201/9781315371733-7.

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Patel, Krishnakumar V., and Prem R. Patel. "Numerical Analysis of the Pressure, Temperature, and Aerodynamic Forces on Hypersonic Blunt Hemispherical Shaped Body." In Recent Advances in Computational Mechanics and Simulations, 363–74. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-8315-5_31.

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Conference papers on the topic "Aerodynamic pressure"

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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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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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KAYSER, L., W. CLAY, and W. DAMICO, JR. "Surface pressure measurements on a 155mm projectile in free-flight at transonic speeds." In 14th Aerodynamic Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-785.

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