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Bibliografías temáticas / Airplanes, Tailless. Airplanes Fluid dynamics

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Literatura académica sobre el tema "Airplanes, Tailless. Airplanes Fluid dynamics"

Autor: Grafiati

Publicado: 4 de junio de 2021

Última modificación: 4 de febrero de 2022

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Artículos de revistas sobre el tema "Airplanes, Tailless. Airplanes Fluid dynamics"

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Olejnik, Aleksander, Łukasz Kiszkowiak y Adam Dziubiński. "Aerodynamic analysis of General Aviation airplanes using computational fluid dynamics methods". Mechanik 90, n.º 8-9 (11 de septiembre de 2017): 802–4. http://dx.doi.org/10.17814/mechanik.2017.8-9.118.

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The problems of an aircraft aerodynamic analysis based on the example of Very Light Aeroplanes and Very Light Jet category airplanes have been presented. A numerical calculations using finite volume method implemented in specialized software were performed. A method of preparing a numerical model of an airplane and the aerodynamic analysis methodology have been presented. An influence of an airplane propulsion on aerodynamic characteristics have been analyzed. A results have been shown in the graphs form of aerodynamic force and moment components as function of angle of attack.

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2

Sieradzki, Adam, Adam Dziubiński y Cezary Galiński. "Performance Comparison of the Optimized Inverted Joined Wing Airplane Concept and Classical Configuration Airplanes". Archive of Mechanical Engineering 63, n.º 3 (1 de septiembre de 2016): 455–70. http://dx.doi.org/10.1515/meceng-2016-0026.

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Abstract The joined wing concept is an unconventional airplane configuration, known since the mid-twenties of the last century. It has several possible advantages, like reduction of the induced drag and weight due to the closed wing concept. The inverted joined wing variant is its rarely considered version, with the front wing being situated above the aft wing. The following paper presents a performance prediction of the recently optimized configuration of this airplane. Flight characteristics obtained numerically were compared with the performance of two classical configuration airplanes of similar category. Their computational fluid dynamics (CFD) models were created basing on available documentation, photographs and some inverse engineering methods. The analysis included simulations performed for a scale of 3-meter wingspan inverted joined wing demonstrator and also for real-scale manned airplanes. Therefore, the results of CFD calculations allowed us to assess the competitiveness of the presented concept, as compared to the most technologically advanced airplanes designed and manufactured to date. At the end of the paper, the areas where the inverted joined wing is better than conventional airplane were predicted and new research possibilities were described.

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3

Secco, Ney Rafael y Bento Silva de Mattos. "Artificial neural networks to predict aerodynamic coefficients of transport airplanes". Aircraft Engineering and Aerospace Technology 89, n.º 2 (6 de marzo de 2017): 211–30. http://dx.doi.org/10.1108/aeat-05-2014-0069.

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Purpose Multidisciplinary design frameworks elaborated for aeronautical applications require considerable computational power that grows enormously with the utilization of higher fidelity tools to model aeronautical disciplines like aerodynamics, loads, flight dynamics, performance, structural analysis and others. Surrogate models are a good alternative to address properly and elegantly this issue. With regard to this issue, the purpose of this paper is the design and application of an artificial neural network to predict aerodynamic coefficients of transport airplanes. The neural network must be fed with calculations from computational fluid dynamic codes. The artificial neural network system that was then developed can predict lift and drag coefficients for wing-fuselage configurations with high accuracy. The input parameters for the neural network are the wing planform, airfoil geometry and flight condition. An aerodynamic database consisting of approximately 100,000 cases calculated with a full-potential code with computation of viscous effects was used for the neural network training, which is carried out with the back-propagation algorithm, the scaled gradient algorithm and the Nguyen–Wridow weight initialization. Networks with different numbers of neurons were evaluated to minimize the regression error. The neural network featuring the lowest regression error is able to reduce the computation time of the aerodynamic coefficients 4,000 times when compared with the computing time required by the full potential code. Regarding the drag coefficient, the average error of the neural network is of five drag counts only. The computation of the gradients of the neural network outputs in a scalable manner is possible by an adaptation of back-propagation algorithm. This enabled its use in an adjoint method, elaborated by the authors and used for an airplane optimization task. The results from that optimization were compared with similar tasks performed by calling the full potential code in another optimization application. The resulting geometry obtained with the aerodynamic coefficient predicted by the neural network is practically the same of that designed directly by the call of the full potential code. Design/methodology/approach The aerodynamic database required for the neural network training was generated with a full-potential multiblock-structured code. The training process used the back-propagation algorithm, the scaled-conjugate gradient algorithm and the Nguyen–Wridow weight initialization. Networks with different numbers of neurons were evaluated to minimize the regression error. Findings A suitable and efficient methodology to model aerodynamic coefficients based on artificial neural networks was obtained. This work also suggests appropriate sizes of artificial neural networks for this specific application. We demonstrated that these metamodels for airplane optimization tasks can be used without loss of fidelity and with great accuracy, as their local minima might be relatively close to the minima of the original design space defined by the call of computational fluid dynamics codes. Research limitations/implications The present work demonstrated the ability of a metamodel with artificial neural networks to capture the physics of transonic and subsonic flow over a wing-fuselage combination. The formulation that was used was the full potential equation. However, the present methodology can be extended to model more complex formulations such as the Euler and Navier–Stokes ones. Practical implications Optimum networks reduced the computation time for aerodynamic coefficient calculations by 4,000 times when compared with the full-potential code. The average absolute errors obtained were of 0.004 and 0.0005 for lift and drag coefficient prediction, respectively. Airplane configurations can be evaluated more quickly. Social implications If multidisciplinary optimization tasks for airplane design become more efficient, this means that more efficient airplanes (for instance less polluting airplanes) can be designed. This leads to a more sustainable aviation. Originality/value This research started in 2005 with a master thesis. It was steadily improved with more efficient artificial neural networks able to handle more complex airplane geometries. There is a single work using similar techniques found in a conference paper published in 2007. However, that paper focused on the application, i.e. providing very few details of the methodology to model aerodynamic coefficients.

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4

Fernstrom, Aaron y Michael Goldblatt. "Aerobiology and Its Role in the Transmission of Infectious Diseases". Journal of Pathogens 2013 (2013): 1–13. http://dx.doi.org/10.1155/2013/493960.

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Aerobiology plays a fundamental role in the transmission of infectious diseases. As infectious disease and infection control practitioners continue employing contemporary techniques (e.g., computational fluid dynamics to study particle flow, polymerase chain reaction methodologies to quantify particle concentrations in various settings, and epidemiology to track the spread of disease), the central variables affecting the airborne transmission of pathogens are becoming better known. This paper reviews many of these aerobiological variables (e.g., particle size, particle type, the duration that particles can remain airborne, the distance that particles can travel, and meteorological and environmental factors), as well as the common origins of these infectious particles. We then review several real-world settings with known difficulties controlling the airborne transmission of infectious particles (e.g., office buildings, healthcare facilities, and commercial airplanes), while detailing the respective measures each of these industries is undertaking in its effort to ameliorate the transmission of airborne infectious diseases.

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Mahdal, Miroslav, Josef Dobeš y Milada Kozubková. "Measurement of Aerodynamic and Acoustic Quantities Describing Flow around a Body Placed in a Wind Tunnel". Measurement Science Review 19, n.º 1 (1 de febrero de 2019): 20–28. http://dx.doi.org/10.2478/msr-2019-0004.

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Abstract Aerodynamically generated noise affects passenger comfort in cars, high-speed trains, and airplanes, and thus, automobile manufacturers aim for its reduction. Investigation methods of noise and vibration sources can be divided into two groups, i.e. experimental research and mathematical research. Recently, owing to the increase in computing power, research in aerodynamically generated noise (aero-acoustics) is beginning to use modern methods such as computational fluid dynamics or fluid-structure interaction. The mathematical model of turbulent flow is given by the system of partial differential equations, its solution is ambiguous and thus requires verification by physical experiment. The results of numerical methods are affected by the boundary conditions of high quality gained from the actual experiment. This article describes an application of complex measurement methodology in the aerodynamic and acoustic (vibro-acoustic) fields. The first part of the paper is focused on the specification of the experimental equipment, i.e. the wind tunnel, which was significantly upgraded in order to obtain the relevant aerodynamics and vibro-acoustics data. The paper presents specific results from the measurement of the aerodynamic and vibro-acoustic fields.

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6

Raeisi, Bahram y Hekmat Alighanbari. "Simulation and analysis of flow around tilting asymmetric ducted fans mounted at the wing tips of a vertical take-off and landing unmanned aerial vehicle". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 232, n.º 15 (3 de julio de 2017): 2870–97. http://dx.doi.org/10.1177/0954410017716954.

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Tilting ducted fans attached to the wing tips of vertical take-off and landing unmanned aerial vehicles define new applications for these types of aerial vehicles. This new configuration gives vertical take-off and landing unmanned aerial vehicles the ability to hover like helicopters and fly forward like airplanes, which results in using any arbitrary location for take-off and landing combined with increasing range and speed. Furthermore, generating additional lift using asymmetrical shape for the external body of the ducted fans can lead to reducing the wing area and related overall drag, which results in saving more energy. This research provides experimental results from wind tunnel tests in addition to computational fluid dynamics simulations to investigate the advantages of using an asymmetrical tilting ducted fan instead of a symmetrical one. “actuator disk model” combined with the assumption of “constant delivered power” to the propeller were used successfully to calculate the induced velocity to the rotor plane of the ducted fan in the computational fluid dynamics simulations. The effects of the stall and flow separation on the aerodynamic coefficients were also studied and compared for the symmetrical and asymmetrical ducted fans. Both computational fluid dynamics and experimental results showed noticeable improvement in the lift coefficient using an asymmetrical shape for the external body of the tilting ducted fans.

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7

Thakur, Ruchi y G. Jagadeesh. "Experimental analysis of shock stand-off distance over spherical bodies in high-enthalpy flows". Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 231, n.º 14 (25 de octubre de 2016): 2666–76. http://dx.doi.org/10.1177/0954410016674035.

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The shock stand-off distance for basic spherical models was investigated in the flow regime of 1–2 km/s, a range for which data are unavailable in the open literature. Experiments were conducted on two hypersonic shock tunnels, at five different enthalpy conditions and two types of test gas, and the bow shock was captured using schlieren flow visualization technique. These results were compared with existing empirical relations and a good match was observed. To further corroborate the results, a computational analysis of the same problem was carried out using an in-house computational fluid dynamics code, HiFUN (High Resolution Flow Solver on UNstructured meshes), and the results were again seen to match well with the experiments. The shock stand-off distance is an important parameter for the design of high-speed airplanes, and therefore a solid quantitative understanding of this parameter is vital for all flow regimes. This paper aims to fill in the gap by investigating one of those regimes where available data are currently missing.

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8

Figat, Marcin y Agnieszka Kwiek. "Aerodynamic and static stability investigation into aircraft coupled system to suborbital space flights". Aircraft Engineering and Aerospace Technology 93, n.º 2 (25 de febrero de 2021): 275–83. http://dx.doi.org/10.1108/aeat-05-2020-0085.

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Purpose The aim of the research is to conduct a study into a configuration of an aircraft system with a focus on aerodynamics. In addition, trim condition and static stability constraints were included. The main application of this system is suborbital space flights. The presented concept of a modular airplane system (MAS) consists of two vehicles: a Rocket Plane and a Carrier. Both are designed in tailless configurations but coupled formed a classic tail aircraft configuration, where the Rocket Plane works as the empennage. The most important challenge is to define the mutual position of those two tailless vehicles under the assumption that each vehicle will be operating alone in different flight conditions while joined in one object create a conventional aircraft. Each vehicle configuration (separated and coupled) must fulfil static stability and trim requirements. Design/methodology/approach Aircrafts’ aerodynamic characteristics were obtained using the MGAERO software which is a commercial computing fluid dynamics tool created by AMI Aero. This software uses the Euler flow model. Results from this software were used in the static stability and trim condition analysis. Findings The main outcome of this investigation is a mutual position of the Rocket Plane and the Carrier that fulfils project requirements. Also, the final configuration of both separated vehicles (Rocket Plane and Carrier) and the complete MAS were defined. In addition, it was observed that in the case of classic aircraft configuration which is created by connecting two tailless vehicles increasing horizontal tail arm reduces static stability. This is related to a significantly higher mass ratio of the horizontal tail (the Rocket Plane) with respect to the whole system. Moving backward, the Rocket Plane has a notable effect on a position of a centre of gravity of the whole system static stability. Moreover, the impact of the mutual vehicles’ position (horizontal tail arm) and inclination angle on the coupled vehicle lift to drag ratio was analysed. Research limitations/implications In terms of aerodynamic computation, MGAERO software using an inviscid flow model, therefore, both a friction drag and breakdown of vortex are not considered. But the presented research is for the computation stage of the design, and the MGAERO software guarantees satisfactory accuracy with respect to the relatively low time of computations. The second limitation is that the presented results are for the conceptual stage of the design and dynamic stability constraints were not taken into account. Practical implications The ultimate goal of the coupled aircraft project is to conduct flying tests and the presented result is one of the milestones to achieve this goal. Originality/value A design process for a conventional aircraft configuration is well known however, there are not many examples of vehicles that consist of two coupled aircrafts where both vehicles have similar mass. The unique part of this paper includes results of the investigation of the mutual position of the vehicles that can fly alone, as well as in coupled form. The impact of the position of the centre of gravity on trim conditions and static stability of the coupled configuration was investigated.

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Krajček Nikolić, Karolina, Anita Domitrović y Slobodan Janković. "Estimation of Aerodynamic Coefficients in a Small Subsonic Wind Tunnel". PROMET - Traffic&Transportation 30, n.º 4 (10 de septiembre de 2018): 457–63. http://dx.doi.org/10.7307/ptt.v30i4.2685.

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To apply the experimental data measured in a wind tunnel for a scaled aircraft to a free-flying model, conditions of dynamical similarity must be met or scaling procedures introduced. The scaling methods should correct the wind tunnel data regarding model support, wall interference, and lower Reynolds number. To include the necessary corrections, the current scaling techniques use computational fluid dynamics (CFD) in combination with measurements in cryogenic wind tunnels. There are a few methods that enable preliminary calculations of typical corrections considering specific measurement conditions and volume limitation of test section. The purpose of this paper is to present one possible approach to estimating corrections due to sting interference and difference in Reynolds number between the real airplane in cruise regime and its 1:100 model in the small wind tunnel AT-1. The analysis gives results for correction of axial and normal force coefficients. The results of this analysis indicate that the Reynolds number effects and the problem of installation of internal force balance are quite large. Therefore, the wind tunnel AT-1 has limited usage for aerodynamic coefficient determination of transport airplanes, like Dash 8 Q400 analyzed in this paper.

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Tasca, Andrea Luca, Vittorio Cipolla, Karim Abu Salem y Monica Puccini. "Innovative Box-Wing Aircraft: Emissions and Climate Change". Sustainability 13, n.º 6 (16 de marzo de 2021): 3282. http://dx.doi.org/10.3390/su13063282.

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The PARSIFAL project (Prandtlplane ARchitecture for the Sustainable Improvement of Future AirpLanes) aims to promote an innovative box-wing aircraft: the PrandtlPlane. Aircraft developed adopting this configuration are expected to achieve a payload capability higher than common single aisle analogues (e.g., Airbus 320 and Boeing 737 families), without any increase in the overall dimensions. We estimated the exhaust emissions from the PrandtlPlane and compared the corresponding impacts to those of a conventional reference aircraft, in terms of Global Warming Potential (GWP) and Global Temperature Potential (GTP), on two time-horizons and accounted for regional sensitivity. We considered carbon dioxide, carbonaceous and sulphate aerosols, nitrogen oxides and related ozone production, methane degradation and nitrate aerosols formation, contrails, and contrail cirrus. Overall, the introduction of the PrandtlPlane is expected to bring a considerable reduction of climate change in all the source regions considered, on both the time-horizons examined. Moreover, fuel consumption is expected to be reduced by 20%, as confirmed through high-fidelity Computational Fluid Dynamics (CFD) simulations. Sensitivity of data, models, and metrics are detailed. Impact reduction and mitigation strategies are discussed, as well as the gaps to be addressed in order to develop a comprehensive Life Cycle Assessment on aircraft emissions.

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Tesis sobre el tema "Airplanes, Tailless. Airplanes Fluid dynamics"

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Vishwanathan, Ashwin. "Numerical investigation of wing morphing capabilities applied to a Horten type swept wing geometry". Morgantown, W. Va. : [West Virginia University Libraries], 2007. https://eidr.wvu.edu/etd/documentdata.eTD?documentid=4980.

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Thesis (M.S.)--West Virginia University, 2007.
Title from document title page. Document formatted into pages; contains viii, 58 p. : ill. (some col.). Includes abstract. Includes bibliographical references (p. 51-52).

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Krikellas, Dimitrios. "Improvement of the performance of a turbo-ramjet engine for UAV and missile applications". Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Dec%5FKrikellas.pdf.

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Thesis (M.S. in Applied Physics and M.S. in Aeronautical Engineering)--Naval Postgraduate School, December 2003.
Thesis advisor(s): Garth V. Hobson, Kai E. Woehler. Includes bibliographical references (p. 133). Also available online.

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3

Piper, Ross H. "Design and testing of a combustor for a turbo-ramjet for UAV and missile applications". Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Mar%5FPiper.pdf.

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Thesis (M.S. in Aeronautical Engineering)--Naval Postgraduate School, March 2003.
Thesis advisor(s): Garth V. Hobson, Raymond P. Shreeve. Includes bibliographical references (p. 81-82). Also available online.

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4

Aliaga, Rivera Cristhian Neil. "An unsteady multiphase approach to in-flight icing /". Thesis, McGill University, 2008. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=112552.

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Ice accretion is a purely unsteady phenomenon that is presently approximated by most icing codes using quasi-steady modeling. The accuracy of ice prediction is thus directly related to the arbitrarily prescribed time span during which the impact of ice growth on both flow and droplets is neglected. The objective of this work is to remove this limitation by implementing a cost-effective unsteady approach. This is done by fully coupling, in time, a diphasic flow (interacting air and droplet particles) with the ice accretion model. The two-phase flow is solved using the Navier-Stokes and Eulerian droplet equations with dual-time stepping in order to improve computational time. The ice shape is either obtained from the conservation of mass and energy within a thin film layer for glaze and mixed icing conditions, or from a mass balance between water droplets impingement and mass flux of ice for rime icing conditions. The iced surface being constantly displaced in time, Arbitrary Lagrangian-Eulerian terms are added to the governing equations to account for mesh movement. Moreover, surface smoothing techniques are developed to prevent degradation of the iced-surface geometric discretization. For rime ice, the numerical results clearly show that the new full unsteady modeling improves the accuracy of ice prediction, compared to the quasi-steady approach, while in addition ensuring time span independence. The applicability of the unsteady icing model for predicting glaze ice accretion is also demonstrated by coupling the diphasic model to the Shallow Water Icing Model. A more rigorous analysis reveals that this model requires the implementation of local surface roughness and that previous quasi-steady validations cannot be carried out using a small number of shots, therefore the need for unsteady simulation.

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5

Nakakita, Kunio. "Toward real-time aero-icing simulation using reduced order models". Thesis, McGill University, 2007. http://digitool.Library.McGill.CA:80/R/?func=dbin-jump-full&object_id=99781.

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Even though the power of supercomputers has increased extraordinarily, there is still an insatiable need for more advanced multi-disciplinary CFD simulations in the aircraft analysis and design fields. A particular current interest is in the realistic three-dimensional fully viscous turbulent flow simulation of the highly non-linear aspects of aero-icing. This highly complex simulation is still computationally too demanding in industry, especially when several runs, such as parametric studies, are needed. In order to make such compute-intensive simulations more affordable, this work presents a reduced order modeling approach, based on the "Proper Orthogonal Decomposition", (POD), method to predict a wider swath of flow fields and ice shapes based on a limited number of "snapshots" obtained from complete high-fidelity CFD computations. The procedure of the POD approach is to first decompose the fields into modes, using a limited number of full-calculations snapshots, and then to reconstruct the field and/or ice shapes using those decomposed modes for other conditions, leading to reduced order calculations. The use of the POD technique drastically reduces the computational cost and can provide a more complete map of the performance degradation of an iced aircraft over a wide range of flight and weather conditions.

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Ahuja, Vivek Hartfield Roy J. "Optimization of fuel-air mixing for a scramjet combustor geometry using CFD and a genetic algorithm". Auburn, Ala, 2008. http://hdl.handle.net/10415/1406.

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Barnes, Chris. "A CFD analysis of the download reduction for the V-22 Osprey wing". Morgantown, W. Va. : [West Virginia University Libraries], 2004. https://etd.wvu.edu/etd/controller.jsp?moduleName=documentdata&jsp%5FetdId=3656.

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Thesis (M.S.)--West Virginia University, 2004.
Title from document title page. Document formatted into pages; contains x, 77 p. : ill. (some col.). Includes abstract. Includes bibliographical references (p. 74-77).

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Kuchan, Abigail. "The integration of active flow control devices into composite wing flaps". Thesis, Georgia Institute of Technology, 2012. http://hdl.handle.net/1853/44758.

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Delaying stall is always an attractive option in the aerospace industry. The major benefit of delaying stall is increased lift during takeoff and landings as well as during high angle of attack situations. Devices, such as fluidic oscillators, can be integrated into wing flaps to help delay the occurrence of stall by adding energized air to the airflow on the upper surface of the wing flap. The energized air from the oscillator allows the airflow to remain attached to the upper surface of the wing flap. The fluidic oscillator being integrated in this thesis is an active flow control device (AFC). One common method for integrating any device into a wing flap is to remove a section of the flap and mechanically secure the device. A current trend in the aerospace industry is the increased use of fiber-reinforced composites to replace traditional metal components on aircraft. The traditional methods of device integration cause additional complications when applied to composite components as compared to metal components. This thesis proposes an alternative method for integration of the AFC devices, which occurs before the fabrication of wing flaps is completed and they are attached to the aircraft wing. Seven design concepts are created to reduce the complications from using current methods of integration on composite wing flaps. The concepts are based on four design requirements: aerodynamics, manufacturing, maintenance, and structure. Four of the design concepts created are external designs, which place the AFC on the exterior surface of the wing flap in two types of grooved channels. The other three designs place the AFC inside the wing flap skin and are categorized as internal designs. In order for the air exiting the AFC to reach the upper surface of the wing flap, slots are created in the wing flap skin for the internal designs. Within each of the seven design concepts two design variants are created based on foam or ribbed core types. Prototypes were created for all of the external design AFC devices and the side inserted AFC and retaining pieces. Wing flap prototypes were created for the rounded groove straight AFC design, the semi-circular groove with straight AFC, and the side inserted AFC designs. The wing flaps were created using the VARTM process with a vertical layup for the external designs. The rounded groove and semi-circular groove prototypes each went through three generations of prototypes until an acceptable wing flap was created. The side inserted design utilized the lessons learned through each generation of the external design prototypes eliminating the need for multiple generations. The lessons learned through the prototyping process helped refine the designs and determine the ease of manufacturing to be used in the design evaluation. The evaluation of the designs is based on the four design requirements stated above. The assessment of the designs uses two levels of evaluation matrices to determine the most fitting design concept. As a result of the evaluation, all four of the external designs and one of the internal designs are eliminated. The two remaining internal designs' foam core and ribbed variants are compared to establish the final design selection. The vertically inserted AFC foam core design is the most fitting design concept for the integration of an AFC device into a composite wing flap.

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Ferguson, Kevin M. "Design and cold flow evaluation of a miniature Mach 4 Ramjet". Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Jun%5FFerguson.pdf.

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Thesis (M.S. in Aeronauticl Engineering)--Naval Postgraduate School, June 2003.
Thesis advisor(s): Garth V. Hobson, Raymond P. Shreeve. Includes bibliographical references (p. 67). Also available online.

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10

Xue, Qingluan. "Development of conjugate heat transfer capability to an unstructured flow solver - U²NCLE". Master's thesis, Mississippi State : Mississippi State University, 2005. http://sun.library.msstate.edu/ETD-db/ETD-browse/browse.

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Libros sobre el tema "Airplanes, Tailless. Airplanes Fluid dynamics"

1

Korus, Andreas. Experimentelle und theoretische Untersuchungen über den Strahleinfluss bei der Umströmung eines Bypass-Triebwerkes. Köln: Deutsche Forschungsanstalt für Luft- und Raumfahrt, 1993.

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Garodz, Leo J. Vortex characteristics of C5A/B, C141B, and C130E aircraft applicable to ATC terminal flight operations tower fly-by data. Silver Spring, Md: U.S. Dept. of Commerce, National Oceanic and Atmospheric Administration, Environmental Research Laboratories, Air Resources Laboratory, 1991.

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Yahya, S. M. Fundamentals of compressible flow: SI units with aircraft and rocket propulsion. 3^a ed. New Delhi: New Age International, 2003.

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1962-, Breitsamter Christian, ed. New results in numerical and experimental fluid mechanics IV: Contributions to the 13th STAB/DGLR Symposium, München, Germany 2002. Berlin: Springer-Verlag, 2004.

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Fejtek, Ian G. Navier-Stokes flowfield computation of wing/rotor interaction for a tilt rotor aircraft in hover. Washington, D. C: Ames Research Center, 1993.

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AG, STAB/DGLR Symposium (10th 1996 Braunschweig Germany). New results in numerical and experimental fluid mechanics: Contributions to the 10th AG STAB/DGLR Symposium, Braunschweig, Germany 1996. Braunschweig/Wiesbaden: Vieweg, 1997.

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Ing, Wagner Siegfried Dr, ed. New results in numerical and experimental fluid mechanics III: Contributions to the 12th STAB/DGLR symposium, Stuttgart, Germany, 2000. Berlin: Springer, 2002.

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1954-, Tropea Cameron, Arbeitsgemeinschaft Strömungen mit Ablösung y Deutsche Gesellschaft für Luft- und Raumfahrt., eds. New results in numerical and experimental fluid mechanics VI: Contributions to the 15th STAB/DGLR Symposium, Darmstadt, Germany, 2006. Berlin: Springer, 2007.

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AG, STAB/DGLR Symposium (11th 1998 Berlin Germany). New results in numerical and experimental fluid mechanics II: Contributions to the 11th AG STAB/DGLR Symposium, Berlin, Germany 1998. Braunschweig/Wiesbaden: Vieweg, 1999.

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Dillmann, Andreas. New Results in Numerical and Experimental Fluid Mechanics VII: Contributions to the 16th STAB/DGLR Symposium Aachen, Germany 2008. Berlin, Heidelberg: Springer Berlin Heidelberg, 2010.

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Capítulos de libros sobre el tema "Airplanes, Tailless. Airplanes Fluid dynamics"

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Flores-García, David, Tiburcio Fernández-Roque y Jorge Hernández-Tamayo. "Vortex in the Wakes of Airplanes". En Fluid Dynamics in Physics, Engineering and Environmental Applications, 345–51. Berlin, Heidelberg: Springer Berlin Heidelberg, 2012. http://dx.doi.org/10.1007/978-3-642-27723-8_31.

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Actas de conferencias sobre el tema "Airplanes, Tailless. Airplanes Fluid dynamics"

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Kandil, Osama, Ihab Adam y Tin-Chee Wong. "Far-field turbulent vortex-wake/exhaust plume interaction for subsonic and HSCT airplanes". En Fluid Dynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1996. http://dx.doi.org/10.2514/6.1996-1962.

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2

Johnson, Forrester, Edward Tinoco y Jong Yu. "Thirty Years of Development and Application of CFD at Boeing Commercial Airplanes, Seattle". En 16th AIAA Computational Fluid Dynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2003. http://dx.doi.org/10.2514/6.2003-3439.

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3

Calay, Rajnish K. y Simon D. Harris. "Investigating Flow Inside a Commercial Aircraft Cabin". En ASME 2002 Pressure Vessels and Piping Conference. ASMEDC, 2002. http://dx.doi.org/10.1115/pvp2002-1460.

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The Computational Fluid Dynamics (CFD) has been used in the Aerospace Industry as a major tool in designing and manufacturing aircraft, however, for the ventilation flows its use is yet to be established. Modern commercial aeroplanes operate in a physically hostile environment. These airplanes contain a complex Environment control and thermal comfort. Therefore there are several numerical modeling issues regarding simulating flows dominated by thermal and convective currents. The ventilation airflow behaviour of the interior of a Boeing 737 is investigated in this paper using CFD.

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4

Tsang, Wing. "Progress in the Development of Chemical Kinetics Databases for the Combustion of Real Fuels". En ASME 2008 International Mechanical Engineering Congress and Exposition. ASMEDC, 2008. http://dx.doi.org/10.1115/imece2008-68369.

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Modern Computational Fluid Dynamics codes have increasing capabilities for taking into account detailed chemical kinetics [1, 2]. This opens the possibility of simulating the combustion of real fuels in industrial devices. This will bring combustion technology in line with modern developments in cutting edge science. One could not design VLSI circuits without simulations. Similarly, the design of modern airplanes depends on simulations before final wind tunnel testing. A key to the proper simulation of the chemistry in combustion is the kinetics database. The aim of this paper is to describe the current situation in this area. We will begin by discussing the special problems posed by the nature of the fuel. We will then define the elements in a proper chemical kinetic database. Currently used databases for the simulation of combustion will be critically examined. The importance of a more fundamentally based database will be emphasized. Finally some recent work pertaining to the chemical kinetics of real liquid fuel molecules will be described.

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5

Zur, Malte, Frank Otremba, Alexander Klippel y Alfred Leder. "Numerical Simulation and Experimental Study of Cabin-Airflow and Transport of Gas-Mixtures in Aircraft Cargo Compartments: Model Validation". En ASME 2013 Fluids Engineering Division Summer Meeting. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/fedsm2013-16622.

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Dangerous goods are transported as air freight in commercial aircrafts. Using plastic jerrycans or plastic containers, liquids or gases can escape by leakage or permeation effects. Prior research by the German Federal Institute for Materials Research and Testing (BAM) showed that the lower explosion limit can be reached when transporting dangerous goods in sea-freight containers under normal transportation situations. This motivated the presented study of the transportation situation of dangerous goods in cargo compartments of commercial airplanes. The scope of this paper is to present the experimental method used for validating a numerical model for CFD (Computational Fluid Dynamics) simulations. The CFD model will be used in a future study to evaluate the potential risk from transporting dangerous goods. The objective of this paper is to present the model mock-up of an aircraft cargo compartment and some examples of three dimensional velocity profiles of the air flow in the mock-up. The velocity profiles are calculated using numerical simulations and measured by Laser-Doppler-Anemometry (LDA) experiments. The mock-up is a generic model of a wide-body aircraft lower deck cargo compartment in a 1:10 scale. Geometry, air exchange rates and inlet as well as outlet flow conditions in the cargo compartment are modeled using realistic boundary conditions. The commercial CFD (Computational Fluid Dynamics) code ANSYS CFX 14 is used for numerical flow simulations applying RANS (Reynolds-Averaged-Navier-Stokes) equations and turbulence models. The turbulence models studied are the renormalization group k-ε-model (RNG), the Reynolds-Stress model by Launder, Reece and Rodi (LRR) and the SST-k-ω-model by Menter (SST). The flow measurement with LDA in the mock-up of a cargo compartment proves to be a feasible method for producing data to validate CFD simulations. Qualitative evaluation of the results shows a good overall agreement between numerical and experimental results. The experimental validation indicates that the implemented CFD model is capable of reproducing the flow situation in the model mock-up.

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Vadake, Kshitij y Jie Cui. "Numerical and Experimental Study of Turbulent Flows Around Clark Y-14 Aerofoil". En ASME 2015 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/imece2015-50536.

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Experimental Fluid Dynamics (EFD) and Computational Fluid Dynamics (CFD) have been instrumental in Fluid Mechanics to help solve scientific and engineering problems. This research attempts to use both techniques to perform a parametric study of turbulence flow around airfoil ClarkY-14 at various velocity and angle of attack (AoA). Clark Y-14 airfoil was designed in the 1920’s. It demonstrated good overall performance at low and moderate Reynolds numbers. With the progress in the aviation field, its performance was sub-optimal for newer aircraft designs. However, with the advent of RC airplanes and model aircrafts, there is a renewed interest in this airfoil. Various research projects have been conducted using this airfoil, but there hasn’t been a combined EFD and CFD study of the performance characteristics of the airfoil itself, which still finds real world applications today. One important aspect of this research included the investigation of the effects of a Force Measurement Device/Sensor, which is typically used in scaled/full-size wind tunnels to mount the test model as well as measure the forces/moments acting on it during the testing. The presence of such a device could affect the quality of the data obtained from the wind tunnel testing when compared to a real world application scenario where the aforementioned device may not be present. To the best of the author’s knowledge, no detailed study has been published on the effects of such devices. In this study, the results with and without the measuring device were generated by using CFD simulations. The results were then compared to see to what extent the inclusion of these devices will affect the results. The methodology used for this research was experimental as well as computational. In the present research, a commercially available CFD software STAR-CCM+ was employed to simulate the flows around airfoil Clark Y-14. The experimental data was obtained from wind tunnel tests using AEROLAB Educational Wind Tunnel (EWT) and compared with the simulation data from the CFD. The two data sets were in good agreement. Both experimental and simulation results were used to understand the effects of the measurement device/sensor used in the scaled wind tunnel on the lift and drag coefficients of the airfoil. Two separate CFD simulation setups were designed to model the presence and absence of the measurement device/sensor. These setups replicated the wind tunnel setup. The airfoil was tested and simulated at different speeds as well as different AoA. The comparative study gave a useful insight on the accuracy of the CFD simulations in relation to the actual testing. The analysis of results concluded that the force measurement device/sensor had insignificant effects on the accuracy and quality of data collected through wind tunnel testing.

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