Relevant bibliographies by topics / Aerodynamic interference

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

Academic literature on the topic 'Aerodynamic interference'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Aerodynamic interference"

1

Wang, Jie, and Jian Xin Liu. "Test Research on Aerodynamic Interference Effect on Aerostatic Coefficients of Main Beam in Parallel Bridge." Applied Mechanics and Materials 178-181 (May 2012): 2131–34. http://dx.doi.org/10.4028/www.scientific.net/amm.178-181.2131.

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Against the problem of the aerodynamic interference effects on aerostatic coefficients between parallel continuous rigid frame bridges with high-pier and long-span, the aerodynamic interference effects on aerostatic coefficients of main beam in the parallel long-span continuous rigid frame bridges were investigated in details by means of wind tunnel test. The space between the two main beams and wind attack angles were changed during the wind tunnel test to study the effects on aerodynamic interferences of aerostatic coefficients of main beam. The test got aerostatic coefficients of 10 conditions. The research results have shown that the aerodynamic interference effects on aerostatic coefficients of main beam in parallel bridges can not be ignored. The aerodynamic interference effects on parallel bridge main beam is shown mainly as follows: The drag coefficient of main beam downstream dropped and the drag coefficient of main beam upstream changed but not change significantly. There are also the aerodynamic interference effects of lateral force coefficient and torque coefficient between the main beams upstream and downstream. The effects upstream are smaller and the effects downstream are larger.
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Wang, Jie, Jin Yun Zhao, and Jian Xin Liu. "Experimental Study of Aerodynamic Interference Effects on Double Thin-Walled Hollow Pier in Tandem Arrangement." Advanced Materials Research 368-373 (October 2011): 1517–20. http://dx.doi.org/10.4028/www.scientific.net/amr.368-373.1517.

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Against the problem of the aerodynamic interference effects on aerostatic coefficients between parallel continuous rigid frame bridges with high-pier and long-span, the aerodynamic interference effects on aerostatic coefficients of double thin-walled hollow pier in the parallel long-span continuous rigid frame bridges were investigated in details by means of wind tunnel test．The space between the two piers and wind direction angles were changed during the wind tunnel test to study the effects on aerodynamic interferences of aerostatic coefficients of twin piers. The test got aerostatic coefficients of 8 conditions. The research results have shown that the aerodynamic interference effects on aerostatic coefficients of double thin-walled hollow pier in parallel bridges can not be ignored. The aerodynamic interference effects on parallel bridge pier is shown mainly as follows: The tandem interval and wind direction angles are important factors affecting interference effects. The drag coefficient of pier downstream dropped and the drag coefficient of pier upstream changed but Not change significantly. There are also the aerodynamic interference effects of lateral force coefficient and torque coefficient between the piers upstream and downstream. The effects upstream are smaller and the effects downstream are larger.
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Wang, Jie, and Jian Xin Liu. "Study of Aerodynamic Interference Effects on Staggered Double Thin-Walled Hollow Pier." Applied Mechanics and Materials 361-363 (August 2013): 1414–17. http://dx.doi.org/10.4028/www.scientific.net/amm.361-363.1414.

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In order to investigate the aerodynamic interference effects between parallel bridges, the aerodynamic interference effects on aerostatic coefficients of double thin-walled hollow pier in the parallel continuous rigid frame bridges with high-pier and long-span were investigated in details by means of wind tunnel test. The tandem interval and side-by-side interval between the two piers and wind direction angles were changed during the wind tunnel test to study the effects on aerodynamic interferences of aerostatic coefficients of twin piers. The test got aerostatic coefficients of 10 conditions. The research results have shown that the aerodynamic interference effects on aerostatic coefficients of double thin-walled hollow pier in parallel bridges can not be ignored. The tandem interval and side-by-side interval between the two piers and wind direction angles are important factors affecting interference effects. The drag coefficient, lateral force coefficient and torque coefficient are affected by these factors.
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Czyż, Zbigniew, and Mirosław Wendeker. "Measurements of Aerodynamic Interference of a Hybrid Aircraft with Multirotor Propulsion." Sensors 20, no. 12 (June 13, 2020): 3360. http://dx.doi.org/10.3390/s20123360.

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This article deals with the phenomenon of aerodynamic interference occurring in the innovative hybrid system of multirotor aircraft propulsion. The approach to aerodynamics requires a determination of the impact of active sources of lift and thrust upon the aircraft aerodynamic characteristics. The hybrid propulsion unit, composed of a conventional multirotor source of thrust as well as lift in the form of the main rotor and a pusher, was equipped with an additional propeller drive unit. The tests were conducted in a continuous-flow low speed wind tunnel with an open measuring space, 1.5 m in diameter and 2.0 m long. Force testing made it possible to develop aerodynamic characteristics as well as defining aerodynamic characteristics and defining the field of speed for the considered design configurations. Our investigations enabled us to analyze the results in terms of a mutual impact of particular components of the research object and the area of impact of active elements present in a common flow.
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Chaplin, Ross, David MacManus, Friedrich Leopold, Bastien Martinez, Thibaut Gauthier, and Trevor Birch. "Aerodynamic Interference on Finned Slender Body." AIAA Journal 54, no. 7 (July 2016): 2017–33. http://dx.doi.org/10.2514/1.j054704.

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Sahu, Jubaraj, Karen R. Heavey, and Earl N. Ferry. "Computational modeling of multibody aerodynamic interference." Advances in Engineering Software 29, no. 3-6 (April 1998): 383–88. http://dx.doi.org/10.1016/s0965-9978(98)00004-0.

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Yahyai, Mahmood, Krishen Kumar, Prem Krishna, and P. K. Pande. "Aerodynamic interference in tall rectangular buildings." Journal of Wind Engineering and Industrial Aerodynamics 41, no. 1-3 (October 1992): 859–66. http://dx.doi.org/10.1016/0167-6105(92)90506-6.

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Vrdoljak, Milan. "Contribution to the propeller aerodynamic interference." PAMM 2, no. 1 (March 2003): 308–9. http://dx.doi.org/10.1002/pamm.200310138.

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Zhang, Jingyu, Mingjin Zhang, Yongle Li, Xu Huang, and Zhong Zheng. "Aerodynamics of High-Sided Vehicles on Truss Girder Considering Sheltering Effect by Wind Tunnel Tests." Baltic Journal of Road and Bridge Engineering 15, no. 2 (June 25, 2020): 66–88. http://dx.doi.org/10.7250/bjrbe.2020-15.473.

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Aerodynamic characteristics of vehicles are directly related to their running safety, especially for the high-sided vehicles. In order to study the aerodynamic characteristics under multiple sheltering conditions, a complex large scale (1:20.4) truss model and three high-sided vehicles including articulated lorry, travelling bus and commercial van models with the same scale were built. The aerodynamic coefficients under various sheltering effects of wind barriers with different heights and porosities, bridge tower and the vehicle on the adjacent lane were measured. According to the results, wind barriers can effectively reduce wind speed behind them, thus decreasing the wind load acting on the vehicle, which causes the decrease of the aerodynamic response of all three vehicles. However, the influence at the leeward side is limited due to installation of central stabilizers. When the vehicle passes through the bridge tower, a sudden change occurs, the aerodynamic coefficients decrease and fluctuate in varying degrees, especially for the commercial van. When the vehicle moves in different lanes behind the bridge tower, the sheltering effect of the tower on the aerodynamic coefficient in Lane 1 is much greater than that in Lane 2. With regard to the interference between two vehicles on the adjacent lanes, the relative windward area between the test vehicle and the interference vehicle greatly affects the aerodynamics of the test vehicle.
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Han, Y., and Steve C. S. Cai. "Aerodynamic Forces of Vehicles on the Bridge under Crosswinds." Advanced Materials Research 639-640 (January 2013): 1206–9. http://dx.doi.org/10.4028/www.scientific.net/amr.639-640.1206.

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In the present study, an experimental setup was made to measure the aerodynamic characteristics of vehicles on the bridge for different cases in a wind tunnel considering the aerodynamic interference. The influence of the wind turbulence, the vehicle interference, and the distance of vehicle from the windward edge of the deck on the aerodynamic coefficients of vehicles were investigated based on the experimental results. The measured results showed that the wind turbulence, the vehicle interference, and the vehicle distance from the windward edge significantly affected the aerodynamic coefficients of vehicles.
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Dissertations / Theses on the topic "Aerodynamic interference"

1

Chaplin, Ross. "Aerodynamic interference between high-speed slender bodies." Thesis, Cranfield University, 2009. http://hdl.handle.net/1826/4520.

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Significant aerodynamic interference can occur between high-speed bodies in close proximity. A complex flowfield develops where shock and expansion waves from a generator body impinge upon the adjacent receiver body. The pressure and flow angularity changes which occur across these disturbances modify the body aerodynamics. The aim of this research is to quantify the aerodynamic interference effects for multi-body configurations and understand the relevant flow physics. The interference aerodynamics for slender bodies in a supersonic flow were investigated through a parametric wind tunnel study. The receiver bodies were finned and un-finned configurations. The effect of lateral and axial body separations, receiver incidence and the strength of the disturbance field were investigated. Measurements included forces and moments, surface pressures and flow visualisations. Supporting computations using steady-state, viscous predictions provided a deeper understanding of the underlying aerodynamics and flow mechanisms. Good agreement was found between the measured and predicted interference loads and surface pressures for all configurations. The interference loads are strongly dependent upon the axial impingement location of the primary shockwave. These induced loads change polarity as the impingement location moves aft over the receiver. The magnitude of the interference loads increase when the receiver is at incidence and are amplified by up to a factor of three when rear fins are attached. In general, the interference loads are larger for a stronger disturbance flowfield. The centre of pressure location is substantially affected and the static stability of the finned receiver changes in some configurations. The effect of the aerodynamic interference on the body trajectories was assessed using an unsteady, Euler prediction in combination with a 6DOF dynamic model. This shows aerodynamic ii interference can cause a collision between the bodies. Moreover, the initial interference loads dominate the subsequent body trajectories and static modelling can be used to evaluate the dynamic trajectories.
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Elzebda, Jamal M. "Two-degree-of-freedom subsonic wing rock and nonlinear aerodynamic interference." Diss., Virginia Polytechnic Institute and State University, 1986. http://hdl.handle.net/10919/50011.

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In many situations the motion of the fluid and the motion of the body must be determined simultaneously and interactively. One example is the phenomenon of subsonic wing rock. A method has been developed that accurately simulates the pitching and rolling motions and accompanying unsteady flowfield for a slender delta wing. The method uses a predictor-corrector technique in conjunction with the general unsteady vortex-lattice method to compute simultaneously the motion of the wing and the flowfield, fully accounting for the dynamic/aerodynamic interaction. For a single degree of freedom in roll, the method predicts the angle of attack at which the symmetric configuration of the leading-edge vortex system becomes unstable, the amplitude, and the period of the resulting self-sustained limit cycle, in close agreement with two wind-tunnel experiments. With the development of modern aerodynamic configurations employing close-coupled canards, such as the X-29, comes the need to simulate unsteady aerodynamic interference. A versatile method based on the general unsteady vortex-lattice technique has been developed. The method yields the time histories of the pressure distribution on the lifting surfaces, the distribution of vorticity in the wakes, and the position of the wakes simultaneously. As an illustration of the method, the unsteady flowfield for a configuration closely resembling the X-29 is presented. The results show the strong influence of the canards on the main wing, including the time lag between the motions of the canards and the subsequent changes in the vorticity and hence the pressure distributions and loads on the main wing.
Ph. D.
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Strachan, Russell K. "The aerodynamic interference effects of side wall proximity on a generic car model." Thesis, Cranfield University, 2010. http://dspace.lib.cranfield.ac.uk/handle/1826/4643.

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The flow around a generic car model both in isolation and in proximity to a near side wall has been investigated utilising experimental and computational methods. Phase one of this investigation tested a range of Ahmed generic road vehicle models with varying backlight angles in isolation, employing laser-Doppler anemometry, static pressure and aerodynamic force and moment measurements in the experimental section. Additionally, numerical simulations were conducted using a commercial Reynolds-averaged Navier Stokes (RANS) code with the RNG k-ε turbulence model. This phase served both to extend the previous knowledge of the flow around the Ahmed model, and analyse the effects of both the supporting strut and rolling road. Phase two then used similar methods to investigate the Ahmed model in proximity to a non-moving side wall. Results from phase two are compared with previous near-wall studies in order that an understanding of the effects of wall proximity can be presented, an area lacking in the existing literature. It is found that the flow on the isolated model must be understood before the effects of side wall proximity can be assessed. There is though, in general, a breakdown of any longitudinal vortices on the near-wall side of the model as model-to-wall distance reduces, with an increase in longitudinal vortex strength on the model side away from the wall. There also exists a large pressure drop on the near-wall model side, which increases in magnitude as model-to-wall distance reduces, before dissipating at separations where the boundary layer restricts the flow. Additionally, there is found to be a pressure drop on the top and bottom of the model with decreasing wall distance, with the relative magnitudes of these dependent on model geometry.
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Leong, Wa-Un Alexis. "A study of aerodynamic and mechanical interference effects between two neighbouring square towers." Thesis, University of Glasgow, 1987. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.311865.

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Strachan, R. K. "The aerodynamic interference effects of side walll proximity on a generic car model." Thesis, Department of Aerospace, Power & Sensors, 2010. http://dspace.lib.cranfield.ac.uk/handle/1826/4643.

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The flow around a generic car model both in isolation and in proximity to a near side wall has been investigated utilising experimental and computational methods. Phase one of this investigation tested a range of Ahmed generic road vehicle models with varying backlight angles in isolation, employing laser-Doppler anemometry, static pressure and aerodynamic force and moment measurements in the experimental section. Additionally, numerical simulations were conducted using a commercial Reynolds-averaged Navier Stokes (RANS) code with the RNG k-ε turbulence model. This phase served both to extend the previous knowledge of the flow around the Ahmed model, and analyse the effects of both the supporting strut and rolling road. Phase two then used similar methods to investigate the Ahmed model in proximity to a non-moving side wall. Results from phase two are compared with previous near-wall studies in order that an understanding of the effects of wall proximity can be presented, an area lacking in the existing literature. It is found that the flow on the isolated model must be understood before the effects of side wall proximity can be assessed. There is though, in general, a breakdown of any longitudinal vortices on the near-wall side of the model as model-to-wall distance reduces, with an increase in longitudinal vortex strength on the model side away from the wall. There also exists a large pressure drop on the near-wall model side, which increases in magnitude as model-to-wall distance reduces, before dissipating at separations where the boundary layer restricts the flow. Additionally, there is found to be a pressure drop on the top and bottom of the model with decreasing wall distance, with the relative magnitudes of these dependent on model geometry.
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Sedlak, Vojtech. "Motorcycle Cornering Improvement : An Aerodynamical Approach based on Flow Interference." Thesis, KTH, Aerodynamik, 2012. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-131200.

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A new aerodynamic device, based on flow interference effects, is studied in order to significantly improve the cornering performance of racing motorcycles in MotoGP. After a brief overview on why standard downforce devices cannot be used on motorcycles, the new idea is introduced and a simplified mechanic analysis is provided to prove its effectiveness. The concept is based on the use of anhedral wings placed on the front fairing, with the rider acting as an interference device, aiming to reduce the lift generation of one wing. Numerical calculations, based on Reynolds-averaged Navier-Stokes equations, are performed on simplified static 2D and 3D cases, as a proof of concept of the idea and as a preparation for further analysis which may involve experimental wind-tunnel testing. The obtained results show that the flow interference has indeed a significant impact on the lift on a single wing. For some cases the lift can be reduced by 70% to over 90% - which strengthens the possibility of a realistic implementation.
Ett nytt aerodynamisk koncept som nyttjar effekter av flödesinterferenser är utvärderat i syfte att på ett noterbart sätt förbättra en roadracing-motorcykels kurtagningsmöjligheter. Efter en kort genomgång av varför diverse klassiska "downforce" lösningar ej är applicerbara på motorcyklar, presenteras det nya konceptet. Varpå en mekanisk analys genomförs i syfte att se över dess tillämpbarhet. Konceptet bygger på anhedrala vingar som placeras på den främre kåpan, där föraren agerar som ett interferensobjekt, och försöker störa ut lyftkraften som den ena vingen genererar. Numeriska beräkningar baserade på RANS-ekvationer är utförda i förenklade statiska 2D och 3D fall. Som ett vidare steg rekommenderas vindtunneltester. Resultaten visar att flödesinterferenser är ytterst märkbara för vingar och i vissa fall kan lyftkraften reducerats med 70-90%. Detta förstäker möjligheten för en realistisk implementering.
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Quickel, Reuben Alexander. "Mount Interference and Flow Angle Impacts on Unshielded Total Temperature Probes." Thesis, Virginia Tech, 2019. http://hdl.handle.net/10919/89952.

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Accurately measuring the total temperature of a high-speed fluid flow is a challenging task that is required in many research areas and industry applications. The difficulty in total temperature measurement generally stems from attempting to minimize measurement error or accurately predict error so it can be accounted for. Conduction error and aerodynamic error are two very common sources of error in total temperature probe measurements. Numerous studies have been performed in prior literature to account for simple cases of both errors. However, the impacts of a mounting strut and freestream flow angle on conduction error and aerodynamic error have not been previously modeled. Both of these effects are very common in gas-turbine applications of total temperature probes. Therefore, a fundamental study was performed to analyze the impact of mount interference and freestream flow angle on a probe's conduction error and aerodynamic error. An experimental study of aerodynamic error was performed using strut-mounted thermocouples in a high-speed jet at Mach numbers ranging from 0.25-0.72. This study showed that a strut stagnation point can provide aerodynamic error reductions and insensitivity to approach Mach number. An off-angle experimental study of conduction error was also performed using strut-mounted thermocouples at pitch angles ranging from -30° to 30°. High-fidelity Computational Fluid Dynamics (CFD) simulations with Conjugate Heat Transfer (CHT) were performed in conjunction with the experiments to provide key heat transfer information and flow visualizations. It was identified that unshielded total temperature probes have reduced conduction error at off-angles, but are sensitive to changes in the freestream flow angle. A low-order method was developed to account for mount interference and flow angle effects. The developed low order method utilizes a local Mach number for aerodynamic error predictions and a local Reynolds number for conduction error predictions. This developed low-order method was validated against experiment and 3D, CFD results, and was shown to accurately capture flow angle trends, mount interference effects, and the impacts of varying probe geometry.
Master of Science
Accurately measuring the total temperature of a high-speed fluid flow is a challenging task that is required in many research areas and industry applications. Many methods exist for measuring total temperature, but the use of thermocouple based probes immersed into a flow remains a common and desirable measurement technique. The difficulty in using thermocouple based probes to acquire total temperature stems from attempting to minimize or accurately predict the probe’s measurement error. Conduction, convection, and radiation heat transfer between the fluid flow and probe create challenges for minimizing measurement error so that the accurate total temperature can be obtained. Numerous studies have been performed in prior literature to account for simple cases of each error source. However, there are many complex, practical applications in which the influence of each error source has not been studied. The impacts of a freestream flow angle and the total temperature probe’s mounting structure have not been previously modeled. Both of these effects are very common in gas-turbine applications of total temperature probes. This Thesis will present a fundamental study analyzing the impact that freestream flow angle and a probe’s mount have on a total temperature probe’s measurement error. The influence of conduction and convection heat transfer was studied experimentally for numerous probe geometries, and the impacts of a mounting strut and freestream flow angle were analyzed. A low-order method was developed to predict conduction error and aerodynamic error for total temperature probes in offangle conditions with the presence of mount interference. The developed low-order method was shown to accurately capture the effects of a mounting strut, varying probe geometry, and varying flow angle. Additionally, the low-order method was validated against experimental and 3D, CFD/CHT results.
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Brown, Kenneth Alexander. "Understanding and Exploiting Wind Tunnels with Porous Flexible Walls for Aerodynamic Measurement." Diss., Virginia Tech, 2016. http://hdl.handle.net/10919/73363.

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The aerodynamic behavior of wind tunnels with porous, flexible walls formed from tensioned Kevlar has been characterized and new measurement techniques in such wind tunnels explored. The objective is to bring the aerodynamic capabilities of so-called Kevlar-wall test sections in-line with those of traditional solid-wall test sections. The primary facility used for this purpose is the 1.85-m by 1.85-m Stability Wind Tunnel at Virginia Tech, and supporting data is provided by the 2-m by 2-m Low Speed Wind Tunnel at the Japanese Aerospace Exploration Agency, both of which employ Kevlar-wall test sections that can be replaced by solid-wall test sections. The behavior of Kevlar fabric, both aerodynamically and mechanically, is first investigated to provide a foundation for calculations involving wall interference correction and determination of the boundary conditions at the Kevlar wall. Building upon previous advancements in wall interference corrections for Kevlar-wall test sections, panel method codes are then employed to simulate the wind tunnel flow in the presence of porous, flexible Kevlar walls. An existing two-dimensional panel method is refined by examining the dependency of correction performance on key test section modeling assumptions, and a novel three-dimensional method is presented. Validation of the interference corrections, and thus validation of the Kevlar-wall aerodynamic performance, is accomplished by comparing aerodynamic coefficients between back-to-back tests of models carried out in the solid- and Kevlar-wall test sections. Analysis of the test results identified the existence of three new mechanisms by which Kevlar walls cause wall-interference. Additionally, novel measurements of the boundary conditions are made during the Kevlar-wall tests to characterize the flow at the boundary. Specifically, digital image correlation is used to measure the global deformation of the Kevlar walls under wind loading. Such data, when used in conjunction with knowledge of the pre-tension in the Kevlar wall and the material properties of the Kevlar, yields the pressure loading experienced by the wall. The pressure loading problem constitutes an inverse problem, and significant effort is made towards overcoming the ill-posedness of the problem to yield accurate wall pressure distributions, as well as lift measurements from the walls. Taken as a whole, this document offers a comprehensive view of the aerodynamic performance of Kevlar-wall test sections.
Ph. D.
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Constanzo, Fernão de Melo. "Análise teórica e experimental da influência da fuselagem sobre a posição do centro aerodinâmico da asa em condições de baixa velocidade." Universidade de São Paulo, 2009. http://www.teses.usp.br/teses/disponiveis/18/18148/tde-13012011-154655/.

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A influência da fuselagem sobre a posição do centro aerodinâmico da asa é complexa e deve ser considerada nos cálculos de equilíbrio e estabilidade estática longitudinal da aeronave. Este trabalho apresenta uma análise comparativa para indicar o mais preciso dentre sete métodos teóricos para prever esta influência, em condições de baixa velocidade, utilizando seis configurações de modelos de asa mais fuselagem em escala reduzida, com proporções dimensionais características da aviação leve. Mediram-se os coeficientes de momento e sustentação para cada configuração, através de ensaios em túnel de vento de baixa velocidade, circuito aberto e seção de testes fechada. Calcularam-se as posições experimentais do centro aerodinâmico através da distância do eixo de rotação da balança ao bordo de ataque da asa e derivadas do coeficiente de momento em relação ao coeficiente de sustentação. Aplicaram-se os métodos teóricos às configurações. Os resultados demonstram que a maioria dos métodos prevê comportamentos na variação da posição do centro aerodinâmico semelhantes aos obtidos experimentalmente e apontados na revisão da literatura. A análise dos resultados teóricos ante os experimentais aponta o método descrito em Engineering Sciences Data Unit (1996a) como o mais preciso.
The fuselage influence on the wing aerodynamic center is complex and must be considered within longitudinal static stability and equilibrium calculations of the airplane. This work presents a comparative analysis to indicate the most accurate between seven theoretical methods that predict this influence, at low speed conditions, using six configurations of wing-fuselage reduced scale models, with the dimensional proportions found in light aviation. The moment and lift coefficients have been measured by experiments in a low speed open circuit wind tunnel with a closed test section. The experimental aerodynamic center positions have been found by the distance of the balance trunnion to wing leading edge and the derivation of the moment coefficient relative to the lift coefficient. The theoretical methods have been applied to all configurations. The results show that most of the methods predict variations in aerodynamic center position in the same way as those obtained in experimental results and shown in the literature review. The analysis between theoretical and experimental results indicates the method from Engineering Sciences Data Unit (1996a) as the most accurate.
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Lee, Jaehyung. "Study on aerodynamic interference and unsteady pressure field around B/D=4 rectangular cylinder based on proper orthogonal decomposition." 京都大学 (Kyoto University), 2006. http://hdl.handle.net/2433/136143.

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Kyoto University (京都大学)
0048
新制・課程博士
博士(工学)
甲第12587号
工博第2700号
新制||工||1388(附属図書館)
UT51-2006-S595
京都大学大学院工学研究科社会基盤工学専攻
(主査)教授 松本 勝, 教授 河井 宏允, 助教授 白土 博通, 教授 田村 武
学位規則第4条第1項該当
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Books on the topic "Aerodynamic interference"

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Baysal, Oktay. Supersonic aerodynamic interference effects of store separation. Norfolk, Va: Dept. of Mechanical Engineering and Mechanics, College of Engineering and Technology, Old Dominion University, 1987.

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West, Michael Gerard. Aerodynamic interference during air-to-air refuelling. Manchester: University ofManchester, 1993.

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D. I. T. P. Llewelyn-Davies. The effect of pitch and yaw on the aerodynamic interference between two identical, unstaggered, axisymmetrical bodies whose centrelines are parallel and separated by 1.11 body diameters. Cranfield, Bedford, England: Cranfield Institute of Technology, College of Aeronautics, 1989.

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Labrujere, Th E. Evaluation of measured-boundary-condition methods for 3D subsonic wall interference. Amsterdam: National Aerospace Laboratory, 1988.

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Britcher, Colin P. Subsonic sting interference on the aerodynamic characteristics of a family of slanted-base ogive-cylinders. Hampton, Va: Langley Research Center, 1990.

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Smith, J. 2D wall interference assessment using "Calspan Pipes". Amsterdam: National Aerospace Laboratory, 1985.

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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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Smith, J. A transonic model representation for two-dimensional wall interference assessment. Amsterdam: National Aerospace Laboratory, 1986.

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Pandey, Ajay K. Finite element thermo-viscoplastic analysis of aerospace structures. Hampton, Va: NASA Langley Research Center, 1990.

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Goodyer, M. J. Derivation of jack movement influence coefficients as a basis for selecting wall contours giving reduced levels of interference in flexible walled test sections. Hampton, VA: National Aeronautics and Space Administration, Langley Research Center, 1985.

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Book chapters on the topic "Aerodynamic interference"

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Fischer, Oliver. "Aerodynamic Development Tools." In Investigation of Correction Methods for Interference Effects in Open-Jet Wind Tunnels, 5–17. Wiesbaden: Springer Fachmedien Wiesbaden, 2018. http://dx.doi.org/10.1007/978-3-658-21379-4_2.

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Fearn, Richard L. "Progress Towards a Model to Describe Jet/Aerodynamic-Surface Interference Effects." In Recent Advances in Aerodynamics, 407–34. New York, NY: Springer New York, 1986. http://dx.doi.org/10.1007/978-1-4612-4972-6_11.

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Mitsumoji, T., Y. Sato, N. Yamazaki, T. Uda, T. Usuda, and Y. Wakabayashi. "Reduction of Aerodynamic Noise Emitted from Pantograph by Appropriate Aerodynamic Interference Around Pantograph Head Support." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 411–21. Cham: Springer International Publishing, 2018. http://dx.doi.org/10.1007/978-3-319-73411-8_31.

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Ren, Nianxin, and Jinping Ou. "Aerodynamic Interference Effect between Large Wind Turbine Blade and Tower." In Computational Structural Engineering, 489–95. Dordrecht: Springer Netherlands, 2009. http://dx.doi.org/10.1007/978-90-481-2822-8_54.

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Liu, Lizhen, and Xiongqing Yu. "A Study on Aerodynamic Interference for Truss Braced Wing Configuration." In Proceedings of the International Conference on Aerospace System Science and Engineering 2020, 129–52. Singapore: Springer Singapore, 2021. http://dx.doi.org/10.1007/978-981-33-6060-0_10.

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Kumar, C. S., and K. P. J. Reddy. "Experimental Investigation of Aerodynamic Interference Heat Transfer Around a Protuberance on a Flat Plate Subjected to Hypersonic Flow." In 28th International Symposium on Shock Waves, 471–76. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-25688-2_72.

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Schoenleber, Christoph, T. Kuthada, Nils Widdecke, F. Wittmeier, and J. Wiedemann. "Investigation of Time-Resolved Nozzle Interference Effects." In Progress in Vehicle Aerodynamics and Thermal Management, 110–31. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-67822-1_7.

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Jakob, H. "The Prediction of Transonic Interference Flow by Means of a Hybrid Method." In Panel Methods in Fluid Mechanics with Emphasis on Aerodynamics, 91–100. Wiesbaden: Vieweg+Teubner Verlag, 1988. http://dx.doi.org/10.1007/978-3-663-13997-3_7.

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"Aerodynamic Interference." In Introduction to Helicopter and Tiltrotor Flight Simulation, 245–66. Reston ,VA: American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/5.9781600862083.0245.0266.

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Frolov, Vladimir. "Optimization of Lift-Curve Slope for Wing-Fuselage Combination." In Aerodynamics. IntechOpen, 2021. http://dx.doi.org/10.5772/intechopen.89056.

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The paper presents results obtained by the author for wing-body interference. The lift-curve slopes of the wing-body combinations are considered. A 2D potential model for cross-flow around the fuselage and a discrete vortex method (DVM) are used. Flat wings of various forms and the circular and elliptical cross sections of the fuselage are considered. It was found that the value of the lift-curve slopes of the wing-body combinations may exceed the same value for an isolated wing. An experimental and theoretical data obtained by other authors earlier confirm this result. Investigations to optimize the wing-body combination were carried within the framework of the proposed model. It was revealed that the maximums of the lift-curve slopes for the optimal midwing configuration with elliptical cross-section body had a sufficiently large relative width (more than 30% of the span wing). The advantage of the wing-fuselage combination with a circular cross section over an isolated wing for wing aspect ratio greater than 6 can reach 7.5% at the relative diameter of fuselage equal to approximately 0.2.
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Conference papers on the topic "Aerodynamic interference"

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ERICSSON, L., and J. REDING. "Dynamic support interference in high alpha testing." In 14th Aerodynamic Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-760.

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Stankowski, Tomasz P., David G. MacManus, Chrisopher T. Sheaf, and Nicholas Grech. "Aerodynamic Interference for Aero-Engine Installations." In 54th AIAA Aerospace Sciences Meeting. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2016. http://dx.doi.org/10.2514/6.2016-0766.

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MACHA, J., and ROBERT BUFFINGTON. "Wall-interference corrections for parachutes in a closed wind tunnel." In 10th Aerodynamic Decelerator Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1989. http://dx.doi.org/10.2514/6.1989-900.

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SICKLES, W., and J. ERICKSON, JR. "Wall interference correction for three-dimensional transonic flows." In 16th Aerodynamic Ground Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-1408.

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Vlachos, Pavlos, and Demetri Telioinis. "Wing-Tip-To-Wing-Tip Aerodynamic Interference." In 41st Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-609.

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RAJAGOPALAN, R., and PAUL KLIMAS. "Aerodynamic interference of two vertical axis wind turbines." In 6th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-2534.

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WOOD, N., and E. ROGERS. "An estimation of the wall interference on a two-dimensional circulation control airfoil." In 14th Aerodynamic Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-738.

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Dyakonov, Artem, Mark Schoenenberger, William Scallion, John Van Norman, Luke Novak, and Chun Tang. "Aerodynamic Interference Due to MSL Reaction Control System." In 41st AIAA Thermophysics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2009. http://dx.doi.org/10.2514/6.2009-3915.

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Hayami, Kaito, Hideaki Sugawara, Yasutada Tanabe, and Masaharu Kameda. "Numerical Investigation of Aerodynamic Interference on Coaxial Rotor." In AIAA Scitech 2020 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2020. http://dx.doi.org/10.2514/6.2020-0306.

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Panneerselvam, S., P. Soundararajan, V. Nagarajan, S. Santhakumar, S. Panneerselvam, P. Soundararajan, V. Nagarajan, and S. Santhakumar. "Dispenser induced aerodynamic interference loads on submunition during dispense." In 15th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-2203.

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Reports on the topic "Aerodynamic interference"

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Dougherty, F. C. Aerodynamic Interference Between Stores. Fort Belvoir, VA: Defense Technical Information Center, January 1992. http://dx.doi.org/10.21236/ada247207.

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Sitek, M. A., C. Bojanowski, and S. A. Lottes. Investigation of Aerodynamic Interference between Twin Deck Bridges. Office of Scientific and Technical Information (OSTI), May 2016. http://dx.doi.org/10.2172/1314092.

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Sahu, Jubaraj, Harris L. Edge, Karen R. Heavey, and Earl N. Ferry. Computational Fluid Dynamics Modeling of Multi-body Missile Aerodynamic Interference. Fort Belvoir, VA: Defense Technical Information Center, August 1998. http://dx.doi.org/10.21236/ada354107.

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