Relevant bibliographies by topics / Transient aerodynamic

Contents

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

Academic literature on the topic 'Transient aerodynamic'

Author: Grafiati
Published: 4 June 2021
Last updated: 6 February 2022

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Journal articles on the topic "Transient aerodynamic"

1

Xiang, Jinwu, Kai Liu, Daochun Li, Chunxiao Cheng, and Enlai Sha. "Unsteady aerodynamic characteristics of a morphing wing." Aircraft Engineering and Aerospace Technology 91, no. 1 (January 7, 2018): 1–9. http://dx.doi.org/10.1108/aeat-04-2017-0101.

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Purpose The purpose of this paper is to investigate the unsteady aerodynamic characteristics in the deflection process of a morphing wing with flexible trailing edge, which is based on time-accurate solutions. The dynamic effect of deflection process on the aerodynamics of morphing wing was studied. Design/methodology/approach The computational fluid dynamic method and dynamic mesh combined with user-defined functions were used to simulate the continuous morphing of the flexible trailing edge. The steady aerodynamic characteristics of the morphing deflection and the conventional deflection were studied first. Then, the unsteady aerodynamic characteristics of the morphing wing were investigated as the trailing edge deflects at different rates. Findings The numerical results show that the transient lift coefficient in the deflection process is higher than that of the static case one in large angle of attack. The larger the deflection frequency is, the higher the transient lift coefficient will become. However, the situations are contrary in a small angle of attack. The periodic morphing of the trailing edge with small amplitude and high frequency can increase the lift coefficient after the stall angle. Practical implications The investigation can afford accurate aerodynamic information for the design of aircraft with the morphing wing technology, which has significant advantages in aerodynamic efficiency and control performance. Originality/value The dynamic effects of the deflection process of the morphing trailing edge on aerodynamics were studied. Furthermore, time-accurate solutions can fully explore the unsteady aerodynamics and pressure distribution of the morphing wing.
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ZHOU, Chao, Yanlai ZHANG, and Jianghao WU. "Aerodynamic periodicity of transient aerodynamic forces of flexible plunging airfoils." Chinese Journal of Aeronautics 34, no. 1 (January 2021): 10–21. http://dx.doi.org/10.1016/j.cja.2020.09.054.

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Huang, Taiming, Zhengqi Gu, Chengjie Feng, and Wei Zeng. "Transient aerodynamics simulations of a road vehicle in the crosswind condition coupled with the vehicle’s motion." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 232, no. 5 (August 11, 2017): 583–98. http://dx.doi.org/10.1177/0954407017704609.

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The influence of transient aerodynamics on a vehicle in a crosswind and the effect on the vehicle’s motion are investigated by employing fully coupled simulations. The fully coupled method makes the simulation data on the fluid dynamics and on the vehicle dynamics exchange in time. LES are used to investigate the movement of the transient turbulence, and wind tunnel experiments are carried out to validate the numerical method. The vehicle is simplified as a three-degree-of-freedom system which moves in only the horizontal direction. The driver’s reaction is considered when the motion of the vehicle is simulated. The results of fully coupled simulations show that the transient aerodynamic loads have a marked influence on the motion of the vehicle. The transitional method of one-way coupled simulations is also employed to obtain data. The simulation results for the two methods are compared with each other. It is found that there is large difference between the results of the two methods. The maximum side force in fully coupled simulations is about 1.22 times the value obtained by the transitional method, and there is a 0.2 m discrepancy between the peak value of the lateral displacement in fully coupled simulations and the peak value in the transitional method. The results show that the transient aerodynamic loads induced by the unsteady motion of the vehicle have a larger effect on the vehicle’s motion than do the aerodynamic loads from the transitional method. Furthermore, the results also reflect the significance of estimating the transient aerodynamic loads in simulations of the vehicle’s motion.
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Shen, Xin, Ping Hu, Jinge Chen, Xiaocheng Zhu, and Zhaohui Du. "The unsteady aerodynamics of floating wind turbine under platform pitch motion." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 232, no. 8 (March 29, 2018): 1019–36. http://dx.doi.org/10.1177/0957650918766606.

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The aerodynamic performance of floating platform wind turbines is much more complex than fixed-base wind turbines because of the flexibility of the floating platform. Due to the extra six degrees-of-freedom of the floating platform, the inflow of the wind turbine rotors is highly influenced by the motions of the floating platform. It is therefore of interest to study the unsteady aerodynamics of the wind turbine rotors involved with the interaction of the floating platform induced motions. In the present work, a lifting surface method with a free wake model is developed for analysis of the unsteady aerodynamics of wind turbines. The aerodynamic performance of the NREL 5 MW floating wind turbine under the prescribed floating platform pitch motion is studied. The unsteady aerodynamic loads, the transient of wind turbine states, and the instability of the wind turbine wakes are discussed in detail.
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Wu, Zhenlong, Can Li, and Yihua Cao. "Numerical Simulation of Rotor–Wing Transient Interaction for a Tiltrotor in the Transition Mode." Mathematics 7, no. 2 (January 22, 2019): 116. http://dx.doi.org/10.3390/math7020116.

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Tiltrotor aerodynamic interaction, especially in the transition mode, is a necessary consideration for tiltrotor aerodynamics, and structural design and optimization. Previous studies have paid much attention to the helicopter mode. However, due to the substantial complexity of the problem, only a small amount of work on the transition mode has been done so far. In this paper, the rotor–wing aerodynamic interaction of a scaled V-22 Osprey tiltrotor, both in the helicopter and transition modes, are studied by computational fluid dynamics (CFD) numerical simulation. The flow field is discretized via the chimera mesh technique and then solved with the Reynolds-averaged Navier–Stokes (RANS) equations. The rotational acceleration of the rotor is considered as a source term added on the right side of the momentum equation of the RANS equations. Both a quasi-steady and a fully transient method are employed to simulate the tilt motion of the rotor in the transition mode. Both qualitative and quantitative results are presented and discussed on the aerodynamic forces, flow physics, and mechanisms. The applicability of the extensively used quasi-steady method for rotor tilt simulation is revealed.
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Hussain, K., H. Rahnejat, and S. Hegazy. "Transient vehicle handling analysis with aerodynamic interactions." Proceedings of the Institution of Mechanical Engineers, Part K: Journal of Multi-body Dynamics 221, no. 1 (March 2007): 21–32. http://dx.doi.org/10.1243/1464419jmbd41.

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Zhang, Zhe, Ying Chao Zhang, and Jie Li. "Vehicles Aerodynamics while Crossing each other on Road Based on Computational Fluid Dynamics." Applied Mechanics and Materials 29-32 (August 2010): 1344–49. http://dx.doi.org/10.4028/www.scientific.net/amm.29-32.1344.

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When vehicles run on road, they will be overtaken, cross by other vehicles or be impacted by crosswind. The other events of overtaking and in crosswind were investigated more deeply. A few of paper report the state of the research on this problem. Until now there are no any wind tunnel and road tests to study on road vehicle aerodynamics while crossing each other. Some numerical simulations were carried out by adopting technology of sliding interface and moving mesh. The method of numerical simulations was narrated in detail. The transient process of vehicles crossing each other was realized. Then the trends of aerodynamic coefficients changing were obtained from the flow field of simulation results. The quantificational changing of vehicles aerodynamic coefficients was obtained when they cross each other. The vehicles are sedan and coach. The simulation results indicated that the all aerodynamic coefficients of two vehicles changed large. The aerodynamic force was important to the vehicles’ handling stability when they cross each other.
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Wu, Da Fang, Shuang Wu, Yue Wu Wang, Zhen Tong Gao, and Jia Ling Yang. "Rapid High-Precision Non-Linear Calibration for Temperature Sensors in Transient Aerodynamic Heating Simulation Systems." Applied Mechanics and Materials 321-324 (June 2013): 618–23. http://dx.doi.org/10.4028/www.scientific.net/amm.321-324.618.

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In order to accurately simulate the transient aerodynamic heating conditions experienced by aircraft when flying at high speeds, rapid and highly precise non-linear dynamic control of the heating process in aerodynamic simulation experiments must be conducted using a transient heat flux control system. This process involves carrying out ‘thermoelectric potential - temperature (E-T)’ conversion of sensors. Here a fast and high-precision ‘E-T’ sensor conversion method for the transient aerodynamic heating control systems of high-speed aircraft is proposed. The developed method has the advantages of easy calculation, rapid conversion speed and high calibration precision, and can thus be employed for fast non-linear dynamic control of rapidly-changing temperature fields in the aerodynamic heating process of high-speed aircraft.
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Chen, Zhen, Zhenqqi Gu, and Tao Jiang. "Research on transient aerodynamic characteristics of windshield wipers of vehicles." International Journal of Numerical Methods for Heat & Fluid Flow 29, no. 8 (August 5, 2019): 2870–84. http://dx.doi.org/10.1108/hff-09-2018-0531.

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Purpose The main purpose of this paper is to gain a better understanding of the transient aerodynamic characteristics of moving windshield wipers. In addition, this paper also strives to illustrate and clarify how the wiper motion impacts the airflow structure; the aerodynamic interaction of two wipers is also discussed. Design/methodology/approach A standard vehicle model proposed by the Motor Industry Research Association and a pair of simplified bone wipers are introduced, and a dynamic mesh technique and user-defined functions are used to achieve the wiper motion. Finite volume methods and large eddy simulation (LES) are used to simulate the transient airflow field. The simulation results are validated through the wind tunnel test. Findings The results obtained from the study are presented graphically, and pressure, velocity distributions, airflow structures, aerodynamic drag and lift force are shown. Significant influences of wiper motion on airflow structures are achieved. The maximum value of aerodynamic lift and drag force exists when wipers are rotating and there is a certain change rule. The aerodynamic lift and drag force when wipers are rotating downward is greater than when wipers are rotating upward, and the force when rotating upward is greater than that when steady. The aerodynamic lift and drag forces of the driver-side wiper is greater than those of the passenger-side wiper. Originality/value The LES method in combination with dynamic mesh technique to study the transient aerodynamic characteristics of windshield wipers is relatively new.
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Wu, Da Fang, Yue Wu Wang, Shuang Wu, Jia Ling Yang, and Zhen Tong Gao. "Research on Control of Heat Flux Environment Simulation for High-Speed Aircraft." Advanced Materials Research 705 (June 2013): 528–33. http://dx.doi.org/10.4028/www.scientific.net/amr.705.528.

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The characteristics of the transient heating control process of aerodynamic simulation experiments are complicated, transient, highly nonlinear, and strongly coupled, which make it difficult or impossible to develop a mathematical model. By using the fuzzy control method, many good qualities (such as robustness, high adaptability to changing parameters, and a short transition process time) can be obtained. Based on the fuzzy control method, a transient aerodynamic heating simulation control system for missiles was established. It was demonstrated that quick dynamic control of the aerodynamic simulation heating process according to the transient and continual change in heat flow on the surface of high-speed aircrafts can be completed by using this control system.
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Dissertations / Theses on the topic "Transient aerodynamic"

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Cairns, Robert Stuart. "Lateral aerodynamic characteristics of motor vehicles in transient crosswinds." Thesis, Cranfield University, 1994. http://hdl.handle.net/1826/2507.

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Motor car crosswind stability can be adversely affected by reductions in both vehicle mass and drag coefficient. As these are two likely results of future developments the importance of research into vehicle aerodynamic stability is set to increase, moreover, there is evidence that transient effects will be the critical. An experimental facility has been designed and constructed and tests have been carried out to investigate the implications of simulating dynamic flow-fields. Vehicle models of approximately 1/6th scale have been propelled along a test track, in the laboratory, to pass through a simulated crosswind gust of variable resultant yaw angle. Force and moment measurements have shown the aerodynamic inputs to be highly repeatable, though the technique has been restricted somewhat by the presence of mechanical "noise". Additional dynamic yaw experiments were conducted on a bluff-body model mounted in the College of Aeronautics' Oscillatory Facility. In some ways this technique is not as realistic as the Crosswind Track in its simulation of the full scale flow, however, despite its simplicity valuable aerodynamic data was derived from this test. Quasi-static tests have also been conducted and demonstrate that for certain model configurations a clearly defined yaw angle range exists where two different wake flow-structures are possible. At any given yaw angle, the dominant structure is determined by the flowfield history - essentially the direction in which the model is moved. This causes hysteresis in the forces and moments generated. In such a situation the flow is referred to as being bi¬stable. Both track and dynamic yaw tests indicate that the bi-stable flow phenomenon, witnessed in quasi-static experiments, can influence the dynamic forces and moments measured on a model. The flow structures associated with bi-stability are viscous-dominated and the slow development of viscous loads can be an important feature. It is possible that various vehicle configurations could induce bi-stable flow. If such flow behaviour is apparent then quasi-static forces and moment measurements will not provide an adequate engineering estimate of the transient aerodynamic loads. In this event it is imperative that the automotive engineer conducts investigations into the vehicle's dynamic performance.
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Atkins, Nicholas Robert. "Aerodynamic performance measurements in a transient turbine test facility." Thesis, University of Oxford, 2005. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.424855.

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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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Mansor, Shuhaimi. "Estimation of bluff body transient aerodynamic loads using an oscillating model rig." Thesis, Loughborough University, 2006. https://dspace.lboro.ac.uk/2134/13208.

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A method for the estimation of transient aerodynamic data from dynamic wind tunnel tests has been developed and employed in the study of the unsteady response of simple automotive type bodies. The experimental setup consists of the test model mounted to the oscillating model facility such that it is constrained to oscillate with a single degree of freedom of pure yawing motion. The yaw position is recorded from a potentiometer and the time response provides the primary measurement. Analysis of the wind-off and wind-on response allows the transient aerodynamic loads to be estimated. The frequency of oscillation, (synonymous with the frequency of disturbing wind input) is modified by altering the mechanical stiffness of the facility. The effects of Reynolds number and oscillation frequency are considered and the model is shown to exhibit damped, self-sustained and self-excited behaviour. The transient results are compared with a quasi-steady prediction based on conventional tunnel balance data and presented in the form of aerodynamic magnification factor. The facility and analysis techniques employed are presented and the results of a parametric study of model rear slant angle and of the influence of C-pillar strakes is reported. The results are strongly dependent on shape but for almost all rear slant angles tested the results show that the transient response exceeds that predicted from steady state data. The level of unsteadiness is also significantly influenced by the rear slant angles. The addition of C-pillar strakes is shown to stabilise the flow with even small strakes yielding responses below that of steady state. From the simulation results the self-sustained oscillation is shown to occur when the aerodynamic damping cancels the mechanical damping. The unsteadiness in the oscillation can be simulated by adding band-limited white noise with an intensity close to that of the turbulence intensity found in the wake. From vehicle crosswind simulation results the aerodynamic yaw moment derivative and its magnification factor are shown to be the important parameters influencing the crosswind sensitivity and path deviation.
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Heinlein, Gregory S. "Aerodynamic Behavior of Axial Flow Turbomachinery Operating in Transient Transonic Flow Regimes." The Ohio State University, 2019. http://rave.ohiolink.edu/etdc/view?acc_num=osu1573149943024303.

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Slater, J. T. D. "Three-dimensional aerodynamic studies of a turbine stage in a transient flow facility." Thesis, University of Oxford, 1993. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.358729.

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Ryan, Anthony G. "The simulation of transient cross-wind gusts and their aerodynamic influence on passenger cars." Thesis, Durham University, 2000. http://etheses.dur.ac.uk/1203/.

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The unique University of Durham transient cross-wind facility has been developed such that sharp edged, finite length, cross-wind gusts with a relative yaw angle of 22' can be developed at the rate of 1000/hr. This cross-wind facility uses the transient interaction of two wind tunnel jets to create these gusts, with the fully automated, rapid, repeatable gust production process allowing ensemble averaging to significantly improve data quality. The cross-wind gust characteristic, as observed for the empty working section, has some inherent problems. A yaw angle undershoot, and more importantly, an overshoot occur at the leading edge of the gust. A transient total pressure overshoot is also observed at the leading edge of the gust. Computational fluid dynamics (CFD) simulations of the empty working section have replicated these anomalies, and suggestions are proposed for their elimination. Two aerodynamic models were tested in this facility, each being subjected to transient cross-wind gusts of 10 model lengths. Both models exhibited significant transient force and moment overshoots. These overshoots were found to be a consequence of delayed pressure development in regions of separated flow, with full flow development requiring up to seven model lengths of cross-wind gust. These results, which cannot be replicated by any steady testing procedure, confirm the requirement for transient testing, if transient forces and moments are required.
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Sheard, A. G. "Aerodynamic and mechanical performance of a high-pressure turbine stage in a transient wind tunnel." Thesis, University of Oxford, 1989. http://ora.ox.ac.uk/objects/uuid:73ecb15e-efde-474d-ae30-3f8f7e1d6f4e.

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Unsteady three-dimensional flow phenomena have major effects on the aerodynamic performance of, and heat transfer to, gas-turbine blading. Investigation of the mechanisms associated with these phenomena requires an experimental facility that is capable of simulating a gas turbine, but at lower levels of temperature and pressure to allow conventional measurement techniques. This thesis reports on the design, development and commissioning of a new experimental facility that models these unsteady three-dimensional flow phenomena. The new facility, which consists of a 62%-size, high-pressure gas-turbine stage mounted in a transient wind tunnel, simulates the turbine design point of a full-stage turbine. The thesis describes the aerodynamic and mechanical design of the new facility, a rigorous stress analysis of the facility’s rotating system and the three-stage commissioning of the facility. The thesis concludes with an assessment of the turbine stage performance.
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Funk, Robert Brent. "Transient interaction between a rotor wake and a lifting surface." Diss., Georgia Institute of Technology, 1995. http://hdl.handle.net/1853/12245.

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Hunt, Dillon C. "Measurement of ablation in transient hypersonic flows /." St. Lucia, Qld, 2001. http://www.library.uq.edu.au/pdfserve.php?image=thesisabs/absthe16475.pdf.

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Books on the topic "Transient aerodynamic"

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Jacobs, Peter A. Transient, hypervelocity flow in an axisymmetric nozzle. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1991.

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Chandrasekhara, M. S. Compressibility effects on dynamic stall of airfoils undergoing rapid transient pitching motion. [Washington, DC: National Aeronautics and Space Administration, 1992.

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Chandrasekhara, M. S. Compressibility effects on dynamic stall of airfoils undergoing rapid transient pitching motion. [Washington, DC: National Aeronautics and Space Administration, 1992.

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Murthy, S. N. B. Transient performance of fan engine with water ingestion. [Washington, DC]: National Aeronautics and Space Administration, U.S. Dept. of Transportation, Federal Aviation Administration, 1993.

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Jacobs, Peter A. Numerical simulation of transient hypervelocity flow in an expansion tube. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1992.

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Jacobs, Peter A. Numerical simulation of transient hypervelocity flow in an expansion tube. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1992.

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Jacobs, Peter A. Numerical simulation of transient hypervelocity flow in an expansion tube. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1992.

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Schulte-Werning, Burkhard, Rémi Grégoire, Antonio Malfatti, and Gerd Matschke, eds. TRANSAERO — A European Initiative on Transient Aerodynamics for Railway System Optimisation. Berlin, Heidelberg: Springer Berlin Heidelberg, 2002. http://dx.doi.org/10.1007/978-3-540-45854-8.

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Moore, F. K. A theory of post-stall transients in multistage axial compression systems. [Washington, D.C.?]: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

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Forum on Unsteady Flow (4rd 1987 Boston, Mass.). Forum on Unsteady Flow - 1987: Presented at the Winter Annual Meeting of the American Society of Mechanical Engineers, Boston, Massachusetts, December 13-18, 1987. New York, N.Y. (345 E. 47th St., New York 10017): ASME, 1987.

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Book chapters on the topic "Transient aerodynamic"

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Alajbegovic, Ales, B. Duncan, and J. Gargoloff. "On-road aerodynamic efficiency under realistic transient wind conditions." In Proceedings, 1521–36. Wiesbaden: Springer Fachmedien Wiesbaden, 2014. http://dx.doi.org/10.1007/978-3-658-05130-3_106.

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Roohani, H., and B. W. Skews. "Transient aerodynamic forces experienced by aerofoils in accelerated motion." In Shock Waves, 1065–70. Berlin, Heidelberg: Springer Berlin Heidelberg, 2009. http://dx.doi.org/10.1007/978-3-540-85181-3_44.

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Wu, Feng, Limin Gao, Xinyun Wu, Xudong Feng, Lintao Leng, and Yaoyu Li. "Aerodynamic Modeling and Transient Performance Improvement of a Free Jet Altitude Test Facility." In Communications in Computer and Information Science, 618–30. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-8101-4_55.

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Elofsson, Per, Guillaume Mercier, Bradley D. Duncan, and Samuel Boissinot. "Accurate Drag Prediction Using Transient Aerodynamics Simulations for a Heavy Truck in Yaw Flow." In The Aerodynamics of Heavy Vehicles III, 343–60. Cham: Springer International Publishing, 2015. http://dx.doi.org/10.1007/978-3-319-20122-1_22.

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Antes, H. "Time Domain Boundary Element Solutions of Hyperbolic Equations for 2-D Transient Wave Propagation." In Panel Methods in Fluid Mechanics with Emphasis on Aerodynamics, 35–42. Wiesbaden: Vieweg+Teubner Verlag, 1988. http://dx.doi.org/10.1007/978-3-663-13997-3_2.

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Bruch, E., and S. Grilli. "Computation of the Transient Flow in Zoned Anisotropic Porous Media by the Boundary Element Method." In Panel Methods in Fluid Mechanics with Emphasis on Aerodynamics, 43–51. Wiesbaden: Vieweg+Teubner Verlag, 1988. http://dx.doi.org/10.1007/978-3-663-13997-3_3.

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Evans, B. J., O. Hassan, J. W. Jones, K. Morgan, and L. Remaki. "Simulating Steady State and Transient Aerodynamic Flows Using Unstructured Meshes and Parallel Computers." In Computational Fluid Dynamics Review 2010, 1–27. WORLD SCIENTIFIC, 2010. http://dx.doi.org/10.1142/9789814313377_0001.

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C. Mehta, Rakhab. "Influence of Input Parameters on the Solution of Inverse Heat Conduction Problem." In Inverse Heat Conduction and Heat Exchangers. IntechOpen, 2020. http://dx.doi.org/10.5772/intechopen.91000.

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A one-dimensional transient heat conduction equation is solved using analytical and numerical methods. An iterative technique is employed which estimates unknown boundary conditions from the measured temperature time history. The focus of the present chapter is to investigate effects of input parameters such as time delay, thermocouple cavity, error in the location of thermocouple position and time- and temperature-dependent thermophysical properties. Inverse heat conduction problem IHCP is solved with and without material conduction. A two-time level implicit finite difference numerical method is used to solve nonlinear heat conduction problem. Effects of uniform, nonuniform and deforming computational grids on the estimated convective heat transfer are investigated in a nozzle of solid rocket motor. A unified heat transfer analysis is presented to obtain wall heat flux and convective heat transfer coefficient in a rocket nozzle. A two-node exact solution technique is applied to estimate aerodynamic heating in a free flight of a sounding rocket. The stability of the solution of the inverse heat conduction problem is sensitive to the spatial and temporal discretization.
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Conference papers on the topic "Transient aerodynamic"

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MAGARI, PATRICK, and JOHN LAGRAFF. "An isentropic compression heated Ludwieg tube transient wind tunnel." In 15th Aerodynamic Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-2019.

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Oettle, Nicholas, Oliver Mankowski, David Sims-Williams, Robert Dominy, Claire Freeman, and Adrian Gaylard. "Assessment of a Vehicle's Transient Aerodynamic Response." In SAE 2012 World Congress & Exhibition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 2012. http://dx.doi.org/10.4271/2012-01-0449.

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CHIANG, TING-LUNG, and KLAUS HOFFMANN. "Transient aerodynamic computation of high speed projectiles." In 28th Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-64.

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Packard, Nathan, and Jeffrey Bons. "Transient Aerodynamic Response To Leading Edge Flow Control." In 6th AIAA Flow Control Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-2805.

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Bao, Hai-tao. "Transient Aerodynamic Numerical of Trains Crossing in Tunnel." In 2011 Fourth International Conference on Information and Computing (ICIC). IEEE, 2011. http://dx.doi.org/10.1109/icic.2011.139.

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Okumura, Kenji, and Toshihiko Kuriyama. "Transient Aerodynamic Simulation in Crosswind and Passing an Automobile." In SAE International Congress and Exposition. 400 Commonwealth Drive, Warrendale, PA, United States: SAE International, 1997. http://dx.doi.org/10.4271/970404.

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Atkins, N. R., R. W. Ainsworth, and N. W. Harvey. "Aerodynamic Performance Measurement in a Fully Scaled Transient Turbine Test Facility." In ASME Turbo Expo 2007: Power for Land, Sea, and Air. ASMEDC, 2007. http://dx.doi.org/10.1115/gt2007-27142.

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Abstract:
The practical performance, both the efficiency and durability, of a High-Pressure (HP) turbine depends on many interrelated factors, including both the steady and unsteady aerodynamics and the heat transfer characteristics. The aerodynamic performance of new turbine designs has traditionally been tested in large scale steady flow rigs, but the testing is adiabatic, and the measurement of heat transfer is very difficult. This paper presents the results of turbine aerodynamic performance measurements at the Oxford Rotor Facility (ORF). Transient test facilities such as the Oxford Rotor allow the simultaneous study of turbine performance and heat transfer. The transient operation gives engine representative Mach number, Reynolds number and gas-to-wall temperature ratios, which are key to the aerothermodynamics of a highly-loaded, transonic, HP turbine stage. Time resolved experimental results are presented together with numerical CFD predictions over a 3% range of non-dimensional speed. The precision uncertainty of the measurements has been resolved to a level comparable with the state of the art in steady flow testing, in the region of ±0.3%.
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CHUNG, K., K. LEAMY, and T. COLLINS. "A turbine engine aerodynamic model for in-stall transient simulation." In 21st Joint Propulsion Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1985. http://dx.doi.org/10.2514/6.1985-1429.

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Price, W. W., and J. j. Sanchez-Gasca. "Simplified wind turbine generator aerodynamic models for transient stability studies." In 2006 IEEE PES Power Systems Conference and Exposition. IEEE, 2006. http://dx.doi.org/10.1109/psce.2006.296446.

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Meier, Alexander, and Stefan Schlamp. "Improved Signal Intensity for Transient Grating Spectroscopy Using a PIV Laser." In 25th AIAA Aerodynamic Measurement Technology and Ground Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-2973.

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Reports on the topic "Transient aerodynamic"

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Luttges, Marvin W., Mark S. Miller, Michael C. Robinson, Derek E. Shipley, and David A. Simms. Evidence That Aerodynamic Effects, Including Dynamic Stall, Dictate HAWT Structure Loads and Power Generation in Highly Transient Time Frames. Office of Scientific and Technical Information (OSTI), August 1994. http://dx.doi.org/10.2172/10177826.

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