Bibliographies thématiques / AERODYNAMICS EFFECT

Littérature scientifique sur le sujet « AERODYNAMICS EFFECT »

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Publié le 11 septembre 2023

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Articles de revues sur le sujet "AERODYNAMICS EFFECT"

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Hong, Sungchan, John Eric Goff et Takeshi Asai. « Effect of a soccer ball’s surface texture on its aerodynamics and trajectory ». Proceedings of the Institution of Mechanical Engineers, Part P : Journal of Sports Engineering and Technology 233, no 1 (9 octobre 2018) : 67–74. http://dx.doi.org/10.1177/1754337118794561.

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The effect of a soccer ball’s surface texture on its aerodynamics and flight trajectory is not definitively known. For this study, five soccer balls were used, each having 32 panels with different surface textures. Their aerodynamics were examined via wind-tunnel experiments and then several non-spin trajectories were calculated for each ball. The results showed that the aerodynamic forces acting on a soccer ball change significantly depending on the surface texture of the ball, which in turn influences flight trajectories. The study contributes to an understanding of how a soccer ball’s surface influences the aerodynamics, which may impact the future design and development of soccer balls.
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Chen, Zhao Jun. « Application of Aerodynamics in the Automotive Repair ». Applied Mechanics and Materials 556-562 (mai 2014) : 991–95. http://dx.doi.org/10.4028/www.scientific.net/amm.556-562.991.

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In the development process of the car, the aerodynamics has a strong impact on the automotive research and design. The initial research of aerodynamics focused on reducing air resistance and improving the car's fuel efficiency. Aerodynamic lift and side forces generated has a significant effect on the stability of cars, and even a threat to the safe driving. With the rapid development of automotive performance, the comfort and security of cars have put forward new and higher requirements, wind noise and airflow pollution generated by the aerodynamics have also emerged. How to reduce the adverse effects on the aerodynamics of cars, which is thought about by not only the people of the design, but also the users and maintenance workers in the car. In the course of vehicle maintenance, arising issues of aerodynamics have been gradually received wide attention.
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Eskandary, Keivan, Morteza Dardel, Mohammad Hadi Pashaei et Abdol Majid Kani. « Effects of Aeroelastic Nonlinearity on Flutter and Limit Cycle Oscillations of High-Aspect-Ratio Wings ». Applied Mechanics and Materials 110-116 (octobre 2011) : 4297–306. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.4297.

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In this study aeroelastic characteristics of long high aspect ratio wing models with structural nonlinearities in quasi-steady aerodynamics flows are investigated. The studied wing model is a cantilever wing with double bending and torsional vibrations and with large deflection ability in according to Dowell-Hodges wing model. This wing model is valid for long, straight and thin homogeneous isotropic beams. Aerodynamics model is based on quasi-steady aerodynamic which is valid for aerodynamic flows in low velocity and without wake, viscosity and compressibility effects. The effect of different parameters such as mass ratios and stiffness ratios on flutter and divergence velocities and limit cycle oscillation amplitudes are carefully studied.
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Liu, Jun, Zhengqi Gu, Taiming Huang, Shuya Li, Ledian Zheng et Kai Sun. « Coupled analysis of the unsteady aerodynamics and multi-body dynamics of a small car overtaking a coach ». Proceedings of the Institution of Mechanical Engineers, Part D : Journal of Automobile Engineering 233, no 14 (22 février 2019) : 3684–99. http://dx.doi.org/10.1177/0954407019831559.

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The severe additional aerodynamic loads that are generated on a small car when overtaking a coach have an adverse effect on the car handling stability and its safety. In this article, a two-way coupling of the unsteady aerodynamics and multi-body dynamics is performed in order to study the mutual interactions of a car in an overtaking maneuver with a coach. The unsteady aerodynamic interactions are obtained by using SST (Menter) K-Omega Detached Eddy Simulation and overset mesh technology. The aerodynamics couple the multi-body dynamics, taking into account the effects of the transverse spacing and the cross winds. To validate the necessity of the two-way coupling method, a one-way coupling of the aerodynamics to the vehicle motion is also conducted. Finally, by comparing the aerodynamic loads and the dynamic response of the overtaking car in different overtaking maneuvers between one- and two-way coupling, the results show that it should be considered with two-way coupling analyses of the car while overtaking a coach, particularly under the severe conditions of a lower transverse spacing or the crosswinds.
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Shinde, Yash. « Dimples Effects on a Spoilers Aerodynamics ». International Journal for Research in Applied Science and Engineering Technology 9, no 8 (31 août 2021) : 1851–68. http://dx.doi.org/10.22214/ijraset.2021.37674.

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Abstract: Over the evolution of automobiles, performance, mileage, and grip have dramatically improved. Nevertheless, there have been some improvements, but now the ideal design has been reached for design of engine, airflow & tires, & ergonomics. This means that even very small design improvements could result in high performance enhancements. As fuel is becoming more expensive, the need for improved aerodynamics is becoming more acute. Thus, the purpose of this paper is to examine the effect of golf-like dimples on the aerodynamic properties of a spoiler. As such, numerical calculations and computational fluid dynamics calculations were performed to investigate the impact on aerodynamics and turbulence spoilers with various surface roughness and angle of attack. Based on the recorded data, this test will provide the best information on the appropriate size for the dimple. The data collected on the test model will be used to calculate the drag coefficient, the downforce, and the wake produced at 56 m/s speed, at four different attack angles. Different sizes & depths of dimples will be used to improve the aerodynamics of spoilers, which will improve their downforce, drag force and wake formation. Keywords: spoiler, aerodynamics, dimples, downforce, aerodynamic forces
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Wenhui, Yan, et Zhang Kun. « Effects of Stage Spacing on Contra-Rotating Propeller Aerodynamic Interactions ». Journal of Physics : Conference Series 2478, no 12 (1 juin 2023) : 122013. http://dx.doi.org/10.1088/1742-6596/2478/12/122013.

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Abstract To identify the law of aerodynamic interactions of contra-rotating propellers (CRPs) and improve their aerodynamics, this study investigates the aerodynamic interactions of 4 CRPs (six blades in front and six in back) with different stage spacings using the Reynolds-averaged Navier-Stokes (RANS) equations-based method. The results showed that the CRP whose stage spacing was 0.25 times the propeller diameter delivered the highest average efficiency and that the aerodynamic interactions between the front and rear propellers decreased as the spacing widened, and compared with the rear propeller, the front one was more sensitive to stage spacing due to the aerodynamic interaction-generated thrust fluctuations. It can be seen that stage spacing exerts a significant effect on CRP aerodynamic interactions. Therefore, choosing an appropriate stage spacing in CRP design is of great significance to enhance its aerodynamics.
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Kornev, Nikolai. « On Unsteady Effects in WIG Craft Aerodynamics ». International Journal of Aerospace Engineering 2019 (6 mai 2019) : 1–14. http://dx.doi.org/10.1155/2019/8351293.

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The paper presents the analysis of unsteady forces and their influence on the aerodynamics and motion of a wing-in-ground (WIG) effect craft. Two-dimensional and three-dimensional aerodynamic models based on the potential flow are coupled with time domain simulations in the longitudinal plane. A special attention is paid to the explanation of the dynamic ground effect on both the sink and pitching motions. The influence of unsteady and quasi-steady forces on the dynamic ground effects and the craft motion is analyzed for different heights of flight.
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Guerrero, Alex, et Robert Castilla. « Aerodynamic Study of the Wake Effects on a Formula 1 Car ». Energies 13, no 19 (5 octobre 2020) : 5183. http://dx.doi.org/10.3390/en13195183.

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The high complexity of current Formula One aerodynamics has raised the question of whether an urgent modification in the existing aerodynamic package is required. The present study is based on the evaluation and quantification of the aerodynamic performance on a 2017 spec. adapted Formula 1 car (the latest major aerodynamic update) by means of Computational Fluid Dynamics (CFD) analysis in order to argue whether the 2022 changes in the regulations are justified in terms of aerodynamic necessities. Both free stream and flow disturbance (wake effects) conditions are evaluated in order to study and quantify the effects that the wake may cause on the latter case. The problem is solved by performing different CFD simulations using the OpenFoam solver. The significance and originality of the research may dictate the guidelines towards an overall improvement of the category and it may set a precedent on how to model racing car aerodynamics. The studied behaviour suggests that modern F1 cars are designed and well optimised to run under free stream flows, but they experience drastic aerodynamic losses (ranging from −23% to 62% in downforce coefficients) when running under wake flows. Although the overall aerodynamic loads are reduced, there is a fuel efficiency improvement as the power that is required to overcome the drag is smaller. The modern performance of Ground Effect by means of vortices management represent a very unique and complex way of modelling modern aerodynamics, but at the same time notably compromises the performance of the cars when an overtaking maneuver is intended.
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Xie, Meng, et Xiaoyan Liu. « The influence and application of nonlinear aerodynamics on static derivatives in transonic regime ». Journal of Physics : Conference Series 2512, no 1 (1 mai 2023) : 012007. http://dx.doi.org/10.1088/1742-6596/2512/1/012007.

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Abstract This paper details two static aeroelastic analysis methods applied to a passenger aircraft model with high aspect ratio wing. The influence of nonlinear aerodynamic force on static aeroelastic derivatives in the transonic regime is analysed. The traditional aerodynamic influence coefficient (AIC) matrix method can produce fast and reliable aerodynamic force and is widely used in aeroelastic analysis. However, the AIC matrix computed by linear aerodynamics will lead to some errors in transonic regime because of the nonlinear effect of aerodynamics. By generating the correction matrices, the AIC matrix is modified, and the accuracy of transonic static aeroelastic correction of aerodynamic data can be improved. The static derivatives are compared to the results of the computational fluid dynamics (CFD) / computational structural (CSD) interaction method.
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Duncan, Bradley, Luca D’Alessio, Joaquin Gargoloff et Ales Alajbegovic. « Vehicle aerodynamics impact of on-road turbulence ». Proceedings of the Institution of Mechanical Engineers, Part D : Journal of Automobile Engineering 231, no 9 (10 avril 2017) : 1148–59. http://dx.doi.org/10.1177/0954407017699710.

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The ultimate target for vehicle aerodynamicists is to develop vehicles that perform well on the road in real-world conditions. On the other hand, vehicle development today is performed mostly in controlled settings, using wind tunnels and computational fluid dynamics with artificially uniform freestream conditions and neglecting real-world effects due to road turbulence from the wind and other vehicles. Turbulence on the road creates a non-uniform and fluctuating flow field in which the length scales of the fluctuations fully encompass the length scales of the relevant aerodynamic flow structures around the vehicle. These fluctuations can be comparable in size and strength with the vehicle’s own wake oscillations. As a result, this flow environment can have a significant impact on the aerodynamic forces and on the sensitivity of these forces to various shape changes. Some aerodynamic devices and integral design features can perform quite differently from the way in which they do under uniform freestream conditions. In this paper, unsteady aerodynamics simulations are performed using the lattice Boltzmann method on a detailed representative automobile model with several design variants, in order to explore the effect of on-road turbulence on the aerodynamics and the various mechanisms that contribute to these effects.
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Thèses sur le sujet "AERODYNAMICS EFFECT"

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Doig, Graham Mechanical &amp Manufacturing Engineering Faculty of Engineering UNSW. « Compressible ground effect aerodynamics ». Awarded by:University of New South Wales. Mechanical & ; Manufacturing Engineering, 2009. http://handle.unsw.edu.au/1959.4/44696.

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The aerodynamics of bodies in compressible ground effect flowfields from low-subsonic to supersonic Mach numbers have been investigated numerically and experimentally. A study of existing literature indicated that compressible ground effect has been addressed sporadically in various contexts, without being researched in any comprehensive detail. One of the reasons for this is the difficulty involved in performing experiments which accurately simulate the flows in question with regards to ground boundary conditions. To maximise the relevance of the research to appropriate real-world scenarios, multiple bodies were examined within the confines of their own specific flow regimes. These were: an inverted T026 wing in the low-to-medium subsonic regime, a lifting RAE 2822 aerofoil and ONERA M6 wing in the transonic regime, and a NATO military projectile at supersonic Mach numbers. Two primary aims were pursued. Firstly, experimental issues surrounding compressible ground effect flows were addressed. Potential problems were found in the practice of matching incompressible Computational Fluid Dynamics (CFD) simulations to wind tunnel experiments for the inverted wing at low freestream Mach numbers (<0.3), where the inverted wing was found to experience significant compressible effects even at Mach 0.15. The approach of matching full-scale CFD simulations to scale model testing at an identical Reynolds number but higher Mach number was analysed and found to be prone to significant error. An exploration was also conducted of appropriate ways to conduct experimental tests at transonic and supersonic Mach numbers, resulting in the recommendation of a symmetry (image) method as an effective means of approximating a moving ground boundary in a small-scale blowdown wind tunnel. Issues of scale with regards to Reynolds number persisted in the transonic regime, but with careful use of CFD as a complement to experiments, discrepancies were quantified with confidence. The second primary aim was to use CFD to gain a broader understanding of the ways in which density changes in the flowfield affect the aerodynamic performance of the bodies in question, in particular when a shock wave reflects from the ground plane to interact again with the body or its wake. The numerical approach was extensively verified and validated against existing and new experimental data. The lifting aerofoil and wing were investigated over a range of mid-to-high subsonic Mach numbers (1>M???>0.5), ground clearances and angles of incidence. The presence of the ground was found to affect the critical Mach number, and the aerodynamic characteristics of the bodies across all Mach numbers and clearances proved to be highly sensitive to ground proximity, with a step change in any variable often causing a considerable change to the lift, moment and drag coefficients. At the lowest ground clearances in both two and three dimensional studies, the aerodynamic efficiency was generally found to be less than that of unbounded (no ground) flight for shock-dominated flowfields at freestream Mach numbers greater than 0.7. In the fully-supersonic regime, where shocks tend to be steady and oblique, a supersonic spinning NATO projectile travelling at Mach 2.4 was simulated at several ground clearances. The shocks produced by the body reflected from the ground plane and interacted with the far wake, the near wake, and/or the body itself depending on the ground clearance. The influence of these wave reflections on the three-dimensional flowfield, and their resultant effects on the aerodynamic coefficients, was determined. The normal and drag forces acting on the projectile increased in exponential fashion once the reflections impinged on the projectile body again one or more times (at a height/diameter ground clearance h/d<1). The pitching moment of the projectile changed sign as ground clearance was reduced, adding to the complexity of the trajectory which would ensue.
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Pande, Abhijit. « Effect of struts on aeroacoustics of axisymmetric supersonic inlets ». Thesis, This resource online, 1994. http://scholar.lib.vt.edu/theses/available/etd-07292009-090449/.

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Nikolov, Zhivko. « Effect of upstream turbulence on truck aerodynamics ». Thesis, Linköpings universitet, Mekanisk värmeteori och strömningslära, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:liu:diva-138696.

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The aerodynamic team at SCANIA has discovered the need to investigate the effect of the upstream turbulence conditions on the aerodynamics of the trucks. This need comes from the fact that there are differences between the drag coefficients obtained using computational fluid dynamics (CFD) and the on-road measurements. This difference can lead to wrong predictions of fuel consumption and emissions, which can cause incorrect evaluation of design changes. In this study the problem of modeling upstream turbulence in CFD simulations is addressed together with its effect on the aerodynamics of the trucks. To achieve this, representative values of turbulence intensity and length scale were found from the work of different researchers, who performed on-road measurements for various conditions. These values were then used in a method by Jakob Mann to generate a synthetic turbulence field. This field was then used to generate time varying velocity components, added to the mean velocity at the inlet of a CFD simulation. After the implementation of the method it was discovered that the conditions at the test section of the virtual wind tunnel were representative of the on-road measurements. The results showed drag increase and wake length decrease, similar to previous studies performed on simple geometries. It also showed that the higher mixing of the flow increases the drag by surface pressure increase of forward facing surfaces and pressure decrease at the base. These conclusions may be extended to other bluff body geometries and it shows the importance of good design around gaps. The comparison between two truck geometries showed that a truck with better aerodynamics in a smooth flow shows less drag increase with introduction of upstream turbulence.
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Jones, Marvin Alan. « Mechanisms in wing-in-ground effect aerodynamics ». Thesis, University College London (University of London), 2000. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.343624.

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An aircraft in low-level flight experiences a large increase in lift and a marked reduction in drag, compared with flight at altitude. This phenomenon is termed the 'wing-in-ground' effect. In these circumstances a region of high pressure is created beneath the aerofoil, and a pressure difference is set up between its upper and lower surfaces. A pressure difference is not permitted at the trailing edge and therefore a mechanism must exist, which allows the pressures above and below to adjust themselves to produce a continuous pressure field in the wake. It is the study of this mechanism and its role in the aerodynamics of low-level flight that forms the basis of our investigation
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Xin, Hong. « Development and validation of a generalized ground effect model for lifting rotors ». Diss., Georgia Institute of Technology, 1999. http://hdl.handle.net/1853/11880.

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Pulla, Devi Prasad. « A study of helicopter aerodynamics in ground effect ». Columbus, Ohio : Ohio State University, 2006. http://rave.ohiolink.edu/etdc/view?acc%5Fnum=osu1149869712.

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Molina, Juan. « Aerodynamics of an oscillating wing in ground effect ». Thesis, University of Southampton, 2011. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.582653.

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This research intends to provide new insight into the aerodynamics of wings in ground effect under dynamic motion. This work represents a new step forward in the field of race car aerodynamics, in which steady aerodynamics are well understood. As the first comprehensive study on oscillating wings in ground effect, several modes of oscillation were studied numerically, including heaving, pitching and combined motion of an airfoil and heaving of a wing fitted with endplates. A wide range of reduced frequencies were tested for the simulations at different ride heights, which showed appreciable differences with respect to a stationary wing. The flowfield around the airfoil was obtained by solving the Reynolds-Averaged Navier- Stokes equations, while Detached Eddy Simulation was used for the wing. A dynamic mesh model was implemented to adapt the grid to the wing motion. The results showed other aerodynamic mechanisms in addition to the ground effect, namely the effective incidence and added mass. Stall can be postponed to lower ride heights by increasing the frequency of heaving, while a pitching airfoil can stall below the static stall incidence when placed close to the ground. A stability analysis showed that flutter can occur at low frequencies in heaving motion but increasing the frequency always stabilises the motion. The behaviour of the vortex formed on the inboard face of the endplate is altered by the heaving motion and has an important effect on the downforce generation. Vortex breakdown can be induced or suppressed depending on the frequency and effective incidence. At high frequencies, these vortices interact with counter-rotating trailing edge vortices to form vortex loops that transform into omega vortices in the wake. Additional experiments for a stationary wing serve to qualitatively validate and complement the reference cases.
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Wang, Yi-Ren. « The effect of wake dynamics on rotor eigenvalues in forward flight ». Diss., Georgia Institute of Technology, 1992. http://hdl.handle.net/1853/13031.

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Zarifi-Rad, Farrokh. « Effect of model cooling in periodic transonic flow ». Thesis, Queen's University Belfast, 1991. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.334688.

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Tyll, Jason Scott. « Concurrent Aerodynamic Shape / Cost Design Of Magnetic Levitation Vehicles Using Multidisciplinary Design Optimization Techniques ». Diss., Virginia Tech, 1997. http://hdl.handle.net/10919/40514.

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A multidisciplinary design optimization (MDO) methodology is developed to link the aerodynamic shape design to the system costs for magnetically levitated (MAGLEV) vehicles. These railed vehicles can cruise at speeds approaching that of short haul aircraft and travel just inches from a guideway. They are slated for high speed intercity service of up to 500 miles in length and would compete with air shuttle services. The realization of this technology hinges upon economic viability which is the impetus for the design methodology presented here. This methodology involves models for the aerodynamics, structural weight, direct operating cost, acquisition cost, and life cycle cost and utilizes the DOT optimization software. Optimizations are performed using sequential quadratic programming for a 5 design variable problem. This problem is reformulated using 7 design variables to overcome problems due to non-smooth design space. The reformulation of the problem provides a smoother design space which is navigable by calculus based optimizers. The MDO methodology proves to be a useful tool for the design of MAGLEV vehicles. The optimizations show significant and sensible differences between designing for minimum life cycle cost and other figures of merit. The optimizations also show a need for a more sensitive acquisition cost model which is not based simply on weight engineering. As a part of the design methodology, a low-order aerodynamics model is developed for the prediction of 2-D, ground effect flow over bluff bodies. The model employs a continuous vortex sheet to model the solid surface, discrete vortices to model the shed wake, the Stratford Criterion to determine the location of the turbulent separation, and the vorticity conservation condition to determine the strength of the shed vorticity. The continuous vortex sheet better matches the mechanics of the flow than discrete singularities and therefore better predicts the ground effect flow. The predictions compare well with higher-order computational methods and experimental data. A 3-D extension to this model is investigated, although no 3-D design optimizations are performed. NOTE: An updated copy of this ETD was added on 05/29/2013.
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Livres sur le sujet "AERODYNAMICS EFFECT"

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1913-, Young A. D., et North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development., dir. Scale effects on aircraft and weapon aerodynamics. Neuilly sur Seine, France : AGARD, 1994.

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Haines, A. B. Scale effects on aircraft and weapon aerodynamics. Neuilly sur Seine : Agard, 1994.

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McMillin, S. Naomi. Effect of planform and body on supersonic aerodynamics of multibody configurations. [Washington, DC] : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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McMillin, S. Naomi. Effect of planform and body on supersonic aerodynamics of multibody configurations. [Washington, DC] : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992.

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Rozhdestvensky, Kirill V. Aerodynamics of a Lifting System in Extreme Ground Effect. Berlin, Heidelberg : Springer Berlin Heidelberg, 2000. http://dx.doi.org/10.1007/978-3-662-04240-3.

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T, Suit William, et Langley Research Center, dir. Effect of transition aerodynamics on aeroassist flight experiment trajectories. Hampton, Va : National Aeronautics and Space Administration, Langley Research Center, 1988.

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Raman, G. Initial turbulence effect on jet evolution with and without tonal excitation. [Washington, DC] : National Aeronautics and Space Administration, 1987.

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Darden, Christine M. Effect of leading-edge load constraints on the design and performance of supersonic wings. [Washington, DC] : National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

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Darden, Christine M. Effect of leading-edge load constraints on the design and performance of supersonic wings. [Washington, DC] : National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1985.

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Althoff, Susan L. Effect of blade planform variation on a small-scale hovering rotor. [Washington, D.C.] : National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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Chapitres de livres sur le sujet "AERODYNAMICS EFFECT"

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Huang, Fei, Xuhong Jin, Guoxi Han et Xiao-li Cheng. « Effect of Slip Flow on Aerodynamics ». Dans Lecture Notes in Electrical Engineering, 135–43. Singapore : Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_11.

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Kryvokhatko, Illia. « Effect of Geometric Parameters on Aerodynamic Characteristics ». Dans Aerodynamics of Tandem Wing Aircraft, 97–157. Cham : Springer Nature Switzerland, 2023. http://dx.doi.org/10.1007/978-3-031-23777-5_3.

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Godsk, Kristian. « The Effect of Add-Ons on Wind Turbine Blades ». Dans Handbook of Wind Energy Aerodynamics, 375–92. Cham : Springer International Publishing, 2022. http://dx.doi.org/10.1007/978-3-030-31307-4_17.

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Godsk, Kristian. « The Effect of Add-Ons on Wind Turbine Blades ». Dans Handbook of Wind Energy Aerodynamics, 1–22. Cham : Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-05455-7_17-1.

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Hamed, Awatef A., Widen Tabakoff et Richard Wenglarz. « Erosion, Deposition, and Their Effect on Performance ». Dans Turbine Aerodynamics, Heat Transfer, Materials, and Mechanics, 585–611. Reston, VA : American Institute of Aeronautics and Astronautics, Inc., 2014. http://dx.doi.org/10.2514/5.9781624102660.0585.0612.

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Son, Onur, et Oksan Cetiner. « Effect of Chordwise Flexibility on Flapping Wing Aerodynamics ». Dans Springer Proceedings in Physics, 203–10. Cham : Springer International Publishing, 2016. http://dx.doi.org/10.1007/978-3-319-30602-5_26.

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Nagai, K., et M. Namba. « Effect of Acoustic Control on the Flutter Boundaries of Supersonic Cascade ». Dans Unsteady Aerodynamics and Aeroelasticity of Turbomachines, 165–79. Dordrecht : Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5040-8_11.

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Qu, Qiulin, et Ramesh K. Agarwal. « Chord-dominated Ground-effect Aerodynamics of Fixed-wing UAVs ». Dans Advanced UAV Aerodynamics, Flight Stability and Control, 201–54. Chichester, UK : John Wiley & Sons, Ltd, 2017. http://dx.doi.org/10.1002/9781118928691.ch6.

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Isomura, Kousuke. « The Effect of Blade Vibration Mode on a Flutter in a Transonic Fan ». Dans Unsteady Aerodynamics and Aeroelasticity of Turbomachines, 725–32. Dordrecht : Springer Netherlands, 1998. http://dx.doi.org/10.1007/978-94-011-5040-8_47.

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Rozhdestvensky, Kirill V. « The Aerodynamics of a Lifting System Near Curved Ground ». Dans Aerodynamics of a Lifting System in Extreme Ground Effect, 183–219. Berlin, Heidelberg : Springer Berlin Heidelberg, 2000. http://dx.doi.org/10.1007/978-3-662-04240-3_7.

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Actes de conférences sur le sujet "AERODYNAMICS EFFECT"

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Coulliette, C., et A. Plotkin. « Airfoil ground effect revisited ». Dans 13th Applied Aerodynamics Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-1832.

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Fulton, Alexander B., Genevieve M. Lipp, Jeffrey D. Reid et Brian P. Mann. « Cycling Aerodynamics : The Effect of Rider Position on Aerodynamic Drag ». Dans ASME 2013 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/imece2013-63488.

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Competitive cyclists seek to maximize their efficiency by minimizing the influence of resistive forces. At the high speeds maintained during competition, aerodynamic drag is the primary resistive force. This paper investigates the influence of a cyclist’s body position using models of aerodynamic drag and elucidates the time benefit of various body positions. Mathematical models from prior work, which use cyclist mass and body position angles, have been used to determine the projected frontal area of a cyclist and the aerodynamic drag. Graphical representation of the non-linear relationship between aerodynamic drag and an increasing velocity are also provided. Finally, simulations are produced for a 40 km time trial course, and the results indicate a maximum performance increase of 20.71% due entirely to rider body position when exerting 400 W. We conclude aerodynamic efficiency is crucial in competitive cycling, and its significant correlation with rider body position should not be ignored.
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Chabalko, Christopher, Timothy Fitzgerald, Marcelo Valdez et Balakumar Balachandran. « Flapping Aerodynamics and Ground Effect ». Dans 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-420.

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Kataoka, Takuya, Hiroshi China, Kunio Nakagawa, Kazuo Yanagimoto et Masahiro Yoshida. « Numerical Simulation of Road Vehicle Aerodynamics and Effect of Aerodynamic Devices ». Dans International Congress & Exposition. 400 Commonwealth Drive, Warrendale, PA, United States : SAE International, 1991. http://dx.doi.org/10.4271/910597.

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Kalra, Tarandeep, Vinod K. Lakshminarayan et James Baeder. « Effect of Tip Geometry on a Hovering Rotor in Ground Effect : A Computational Study ». Dans 31st AIAA Applied Aerodynamics Conference. Reston, Virginia : American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-2542.

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Mitchell, D., et S. Raghunathan. « Effect of heat transfer on periodic transonic flows ». Dans 12th Applied Aerodynamics Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1994. http://dx.doi.org/10.2514/6.1994-1903.

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Barlow, Jewel, Rui Guterres et Robert Ranzenbach. « Rectangular bodies with radiused edges in ground effect ». Dans 18th Applied Aerodynamics Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2000. http://dx.doi.org/10.2514/6.2000-4014.

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Barlow, Jewel, Rui Guterres et Robert Ranzenbach. « Rectangular bodies with radiused edges in ground effect ». Dans 17th Applied Aerodynamics Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-3153.

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Kumarasamy, Sanjay, Jewel Barlow, Sanjay Kumarasamy et Jewel Barlow. « Unsteady flow over a hemisphere in ground effect ». Dans 15th Applied Aerodynamics Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-2210.

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Ghosh, Sayan, Mark Lohry et R. Rajagopalan. « Rotor Configurational Effect on Rotorcraft Brownout ». Dans 28th AIAA Applied Aerodynamics Conference. Reston, Virigina : American Institute of Aeronautics and Astronautics, 2010. http://dx.doi.org/10.2514/6.2010-4238.

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Rapports d'organisations sur le sujet "AERODYNAMICS EFFECT"

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Candler, Graham V. Effect of Internal Energy Excitation on Supersonic Blunt-Body Aerodynamics. Fort Belvoir, VA : Defense Technical Information Center, mars 2001. http://dx.doi.org/10.21236/ada387503.

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Paschkewitz, J. A computational study of tandem dual wheel aerodynamics and the effect of fenders and fairings on spray dispersion. Office of Scientific and Technical Information (OSTI), janvier 2006. http://dx.doi.org/10.2172/895084.

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Penetrante, B., et J. Sherohman. Feasibility study for analyzing plasma-aerodynamic effects. Office of Scientific and Technical Information (OSTI), mai 1999. http://dx.doi.org/10.2172/7951.

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Harmon, C. B., et William Dieterich. A 3-Degree-of-Freedom Flight Simulator Evaluation of Unsteady Aerodynamics Effects. Fort Belvoir, VA : Defense Technical Information Center, août 1991. http://dx.doi.org/10.21236/ada241540.

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Miller, Mark S., et Derek E. Shipley. Structural Effects of Unsteady Aerodynamic Forces on Horizontal Axis Wind Turbines. Office of Scientific and Technical Information (OSTI), août 1994. http://dx.doi.org/10.2172/10177977.

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Tilak, Baibhav, et T. K. Jindal. Effect of Co-Flow Jet Characteristic on the Aerodynamic Performance of an Airfoil. Journal of Young Investigators, février 2021. http://dx.doi.org/10.22186/jyi.39.2.22-26.

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Rock, S. G., et S. D. Habchi. Advanced Computational Model for Rocket Plume Effects on Escape System Aerodynamic Characteristics. Fort Belvoir, VA : Defense Technical Information Center, juin 1997. http://dx.doi.org/10.21236/ada353481.

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Cooper, Gene R. The Effects of Aerodynamic Jump Caused by a Uniform Sequence of Lateral Impulses. Fort Belvoir, VA : Defense Technical Information Center, juillet 2004. http://dx.doi.org/10.21236/ada425205.

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Weinacht, Paul. Effect of Body Cross Section on Projectile Aerodynamic Performance With Application to Electromagnetic (EM) Guns. Fort Belvoir, VA : Defense Technical Information Center, avril 2001. http://dx.doi.org/10.21236/ada393427.

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Witte, James. PR-015-17608-R01 Assess and Identify Methods to Reduce Ultrasonic Noise Effects on Ultrasonic Meters. Chantilly, Virginia : Pipeline Research Council International, Inc. (PRCI), juillet 2019. http://dx.doi.org/10.55274/r0011603.

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Ultrasonic noise generated by aerodynamic noise attenuating control valves has been known to have an impact on ultrasonic flow meter performance when the noise characteristic is within the frequency range of the ultrasonic transducers and of great enough amplitude to interfere with ultrasonic signal detection by the flow meter electronics. The intent of this project was to demonstrate the effects of control-valve-generated ultrasonic noise on an ultrasonic flow meter. Flow meter performance characteristics observed when exposed to ultrasonic noise were to be identified, and different methods for potential mitigation of the problem were to be experimentally evaluated. Control valve noise characteristics have been previously evaluated by ultrasonic meter manufacturers and control valve manufacturers. However, the specific ultrasonic frequency spectrum characteristics, which are unique to each control valve noise attenuating trim, are proprietary information held by the manufacturers.
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