Relevant bibliographies by topics / Airplanes Turbulence

Contents

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

Academic literature on the topic 'Airplanes Turbulence'

Author: Grafiati
Published: 4 June 2021
Last updated: 9 February 2022

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Journal articles on the topic "Airplanes Turbulence"

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Tulapurkara, E. G. "Turbulence models for the computation of flow past airplanes." Progress in Aerospace Sciences 33, no. 1-2 (1997): 71–165. http://dx.doi.org/10.1016/s0376-0421(96)00002-4.

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Bäuerle, N., O. Engelhardt-Funke, and M. Kolonko. "ROUTING OF AIRPLANES TO TWO RUNWAYS: MONOTONICITY OF OPTIMAL CONTROLS." Probability in the Engineering and Informational Sciences 18, no. 4 (2004): 533–60. http://dx.doi.org/10.1017/s0269964804184088.

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We consider the problem of routing incoming airplanes to two runways of an airport. Due to air turbulence, the necessary separation time between two successive landing operations depends on the type of airplane. When viewed as a queuing problem, this means that we have dependent service times. The aim is to minimize the waiting times of aircrafts. We consider here a model in which arrivals form a stochastic process and the decision-maker does not know anything about future arrivals. We formulate this as a problem of stochastic dynamic programming and investigate the monotonicity of optimal rou
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Hariyadi, Setyo, Sutardi Sutardi, Wawan Aries Widodo, and Bambang Juni Pitoyo. "Comparative Study of Forward Wingtip Fence and Rearward Wingtip Fence on Wing Airfoil Eppler E562." Journal of Energy, Mechanical, Material, and Manufacturing Engineering 5, no. 1 (2020): 25. http://dx.doi.org/10.22219/jemmme.v5i1.11968.

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The perfect wing is a dream that many airplanes has manufactured have been striving to achieve since the beginning of the airplane design. There are some aspect that most influence in aircraft design lift, drag, thrust, and weight. The combination of these aspects leads to a decrease in fuel consumption, which reduces pollution in our atmosphere and increase in economic revenue. One way to improve aircraft performance is to modify the tip of the wing geometry, which has become a common sight on today’s airplanes. With computational programs, the effects on drag due to wingtip devices can be pr
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Aqilah, Farah, Mazharul Islam, Franjo Juretic, Joel Guerrero, David Wood, and Farid Nasir Ani. "STUDY OF MESH QUALITY IMPROVEMENT FOR CFD ANALYSIS OF AN AIRFOIL." IIUM Engineering Journal 19, no. 2 (2018): 203–12. http://dx.doi.org/10.31436/iiumej.v19i2.905.

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ABSTRACT: Airfoils generate lift in engineering applications such as for airplanes, wind turbines, automotive spoilers, etc. For accurate CFD analysis of airfoils, the quality of the mesh is of paramount importance, especially when dealing with turbulent flows commonly encountered in real life applications. Currently there are different tools that are available to improve the quality of the mesh required for CFD studies. This paper describes a study to assess the significant of the quality of the mesh on CFD analyses of NACA 23012 airfoil by using selected open source tools. The turbulence is
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Majka, Andrzej. "Flight Loads of Mini UAV." Solid State Phenomena 198 (March 2013): 194–99. http://dx.doi.org/10.4028/www.scientific.net/ssp.198.194.

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Designing and building of the unmanned aircraft, especially light and ultra light vehicles, is mainly performed using the experience gained when constructing the flying models. There have not been uniform principles of building and exploiting of the mini and micro UAV (Unmanned Aerial Vehicle) in the form of regulations similar to those for manned airplanes. The unmanned vehicles of these classes in terms of their abilities and attractive price are more frequently exploited using the same air area as manned airplanes performing missions over the inhabited areas. An urgent necessity arises to w
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Xu, Xin, Da Wei Liu, De Hua Chen, and Yuan Jing Wang. "Numerical Investigation on Shock-Induced Separation Structure of Supercritical Airfoil." Advanced Materials Research 756-759 (September 2013): 4502–5. http://dx.doi.org/10.4028/www.scientific.net/amr.756-759.4502.

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The supercritical airfoil has been widely applied to large airplanes for sake of high aerodynamic efficiency. But at transonic speeds, the complicated shock-induced separation on the upper surface of supercritical airfoil will change the aerodynamic characteristics. The transonic flows over a typical supercritical airfoil CH were numerically investigated in this paper, in order to analyses different shock-induced separation structure. The two-dimensional Navier-Stokes equations were solved with structure grids by utilizing the S-A turbulence model. The computation attack angles of CH airfoil v
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Łapka, Piotr, Marije Bakker, Piotr Furmański, and Hans van Tongeren. "Comparison of 1D and 3D thermal models of the nacelle ventilation system in a small airplane." Aircraft Engineering and Aerospace Technology 90, no. 1 (2018): 114–25. http://dx.doi.org/10.1108/aeat-09-2015-0204.

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Purpose Insight in the temperature distribution on the internal and external surface of the nacelle is of great importance during the design phase of an aircraft. However, detailed information is not always needed. In a preliminary project stage or during parametric optimization, short analysis times are often more crucial than high accuracy. In such cases, the global insight in the temperature levels suffices to gain understanding of the relevance and influence of certain parameters. Nevertheless, estimating the maximum temperature for the most adverse conditions should also be done before a
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Aylor, Donald E., Matthew T. Boehm, and Elson J. Shields. "Quantifying Aerial Concentrations of Maize Pollen in the Atmospheric Surface Layer Using Remote-Piloted Airplanes and Lagrangian Stochastic Modeling." Journal of Applied Meteorology and Climatology 45, no. 7 (2006): 1003–15. http://dx.doi.org/10.1175/jam2381.1.

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Abstract The extensive adoption of genetically modified crops has led to a need to understand better the dispersal of pollen in the atmosphere because of the potential for unwanted movement of genetic traits via pollen flow in the environment. The aerial dispersal of maize pollen was studied by comparing the results of a Lagrangian stochastic (LS) model with pollen concentration measurements made over cornfields using a combination of tower-based rotorod samplers and airborne radio-controlled remote-piloted vehicles (RPVs) outfitted with remotely operated pollen samplers. The comparison betwee
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Bruce Ralphin Rose, J., and Gr Jinu. "Gust Induced Aerodynamic Force Prediction on a Transport Wing Using Quasi-Steady Approximation." International Journal of Computational Methods 12, no. 06 (2015): 1550034. http://dx.doi.org/10.1142/s0219876215500346.

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The atmospheric wind turbulence over a specified time period has a strong influence on the airplane performance characteristics. Forecasting of this unsteady aerodynamic phenomenon is complex one for designing the control systems to ensure the structural safety. A novel approach is developed to assess the influence of a gust structure on the aerodynamic coefficients of an airplane. The load factor enhancement because of the discrete gust is also quantified to ensure the safety margin. The Kussner’s function is used to determine the time varying increment of gust-dependent lift produced on an a
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Ma, Tielin, Zhihua Wei, Haibing Chen, and Xiangsheng Wang. "Simulation of the dynamic retrieval process of a towed target system under towing airplane’s wake and atmospheric turbulence." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 9 (2020): 1518–30. http://dx.doi.org/10.1177/0954410020916292.

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This paper studies the dynamic retrieval process of a towed target system under perturbation by simulating the reel-in operation under the towing airplane’s wake and atmospheric turbulence. To settle the computational problem of cable tension, the constant-length method is proposed to transform this variable-mass problem into a constant-length problem based on a mass-spring model that discretizes the cable. A three-dimensional atmospheric turbulence field is built using a recursive function to model the complex perturbation field along the cable. A horseshoe vortex model is adopted to simulate
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Dissertations / Theses on the topic "Airplanes Turbulence"

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Riaz, Jamshed. "A simulation model of atmospheric turbulence for rotorcraft applications." Diss., Georgia Institute of Technology, 1992. http://hdl.handle.net/1853/12940.

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Wee, Teik Khoo. "Cold flow drag measurement and numerical performance prediction of a miniature ramjet at Mach 4." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 2003. http://library.nps.navy.mil/uhtbin/hyperion-image/03Dec%5FWee.pdf.

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Thesis (M.S. in Engineering Science (Mechanical Engineering))--Naval Postgraduate School, December 2003.<br>Thesis advisor(s): Garth V. Hobson, Rayomnd P. Shreeve. Includes bibliographical references (p. 67). Also available online.
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Bowersox, Rodney Dale Welch. "Meanflow and turbulence measurements in the wake of a supersonic through-flow cascade." Thesis, This resource online, 1990. http://scholar.lib.vt.edu/theses/available/etd-03122009-040531/.

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Davis, James Arthur. "Acoustic-vortical-combustion interaction in a solid fuel ramjet simulator." Diss., Georgia Institute of Technology, 1989. http://hdl.handle.net/1853/12947.

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Miki, Kenji. "Simulation of magnetohydrodynamics turbulence with application to plasma-assisted supersonic combustion." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2009. http://hdl.handle.net/1853/26605.

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Thesis (Ph.D)--Aerospace Engineering, Georgia Institute of Technology, 2009.<br>Committee Chair: Menon Suresh; Committee Co-Chair: Jagoda Jeff; Committee Member: Ruffin Stephen; Committee Member: Thorsten Stoesser; Committee Member: Walker Mitchell. Part of the SMARTech Electronic Thesis and Dissertation Collection.
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Dagenhart, J. Ray. "Crossflow stability and transition experiments in a swept-wing flow." Diss., Virginia Tech, 1992. http://hdl.handle.net/10919/39084.

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Zarro, Sarah E. "Steady state and transient measurements within a compressor rotor during steam-induced stall at transonic operational speeds." Thesis, Monterey, California. Naval Postgraduate School, 2006. http://hdl.handle.net/10945/2528.

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Approved for public release, distribution unlimited<br>Steam leakage from an aircraft carrier catapult is sometimes ingested into the aircraft engines upon launch which may induce compressor stall. Investigation of this phenomenon is of particular interest to the Navy with its new F35C, the aircraft carrier variant of the joint strike fighter. The single engine configuration of the F-35C makes this aircraft particularly vunerable to steam-induced stall. The present study examined both throttle-induced stall and steam-induced stall in a compressor at 90% and 95% speed through the use of 9 Kulit
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Zaki, Mina Adel. "Physics based modeling of axial compressor stall." Diss., Atlanta, Ga. : Georgia Institute of Technology, 2009. http://hdl.handle.net/1853/31683.

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Thesis (Ph.D)--Aerospace Engineering, Georgia Institute of Technology, 2010.<br>Committee Chair: Dr. Lakshmi N. Sankar; Committee Member: Dr. Alex Stein; Committee Member: Dr. J.V. R. Prasad; Committee Member: Dr. Richard Gaeta; Committee Member: Dr. Suresh Menon. Part of the SMARTech Electronic Thesis and Dissertation Collection.
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Fleming, Jonathan Lee. "An experimental study of a turbulent wing-body junction and wake flow." Thesis, This resource online, 1991. http://scholar.lib.vt.edu/theses/available/etd-08222009-040300/.

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Mendoza, Jeffrey Michael. "Effects of cavity dimensions, boundary layer, and temperature on cavity noise generation and control." Diss., Georgia Institute of Technology, 1997. http://hdl.handle.net/1853/11959.

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Books on the topic "Airplanes Turbulence"

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Turbulence: A new perspective for pilots. Jeppesen Sanderson Training Systems, 1993.

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Breitsamter, Christian. Turbulente Strömungsstrukturen an Flugzeugkonfigurationen mit Vorderkantenwirbeln. Utz, Wissenschaft, 1997.

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Board, United States National Transportation Safety. Aircraft incident report: In-flight turbulence encounter and loss of portions of the elevators, China Airlines flight CI-012, McDonnell Douglas MD-11-P, Taiwan Registration B-150 about 20 miles east of Japan, December 7, 1992. National Transportation Safety Board, 1994.

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Roberts, L. The generation of side force by distributed section. National Aeronautics and Space Administration, Ames Research Center, 1993.

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United States. National Transportation Safety Board. In-flight turbulence encounter and loss of portions of the elevators: China Airlines flight CI-012, McDonnell Douglas MD-11-P, Taiwan Registration B-150 about 20 miles east of Japan, December 7, 1992. The Board, 1994.

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Tatnall, Christopher Rhoads. An investigation of candidate sensor-observable wake vortex strength parameters for the NASA Aircraft Vortex Spacing System (AVOSS). National Aeronautics and Space Administration, Langley Research Center, 1998.

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United States. National Transportation Safety Board. In-flight engine separation, Japan Airlines, Inc. Flight 46E, Boeing 747-121, N47EV, Anchorage, Alaska, March 31, 1993. The Board, 1993.

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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. Springer-Verlag, 2004.

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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. 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. Springer, 2002.

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Book chapters on the topic "Airplanes Turbulence"

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Brock, Fred V., and Scott J. Richardson. "Dynamic Performance Characteristics, Part 1." In Meteorological Measurement Systems. Oxford University Press, 2001. http://dx.doi.org/10.1093/oso/9780195134513.003.0008.

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When the input to a sensor is changing rapidly, we observe performance characteristics that are due to the change in input and are not related to static performance characteristics. In this chapter we will assume that a static calibration has been applied so that we can consider dynamic performance independently of static characteristics. The terms “linear” and “nonlinear” have been used in chap. 3 in the static sense. Now they are being used in the dynamic sense where “linear” connotes the applicability of the superposition property. A given sensor could be nonlinear in the static sense (e.g., a PRT is nonlinear in that is static sensitivity is not constant over the range) but could be linear in the dynamic sense (modeled by a linear differential equation). We use differential equations to model this dynamic performance while realizing the models can never be exact. If the dynamic behavior of physical systems can be described by linear differential equations with constant coefficients, the analysis is relatively easy because the solutions are well known. Such equations are always approximations to the actual performance of physical systems that are often nonlinear, vary with time, and have distributed parameters. The justification for the use of simple, readily solved models must be the quality of the fit of the solution to the actual system output and the usefulness of the resulting analysis. Dynamic performance characteristics define the way instruments react to measurand fluctuations. When a temperature sensor is mounted on an airplane these characteristics will indicate what the sensor “sees.” If the airplane flies through a cloud with a slow sensor (where time constant is large) it may not register change of temperature or humidity. That would not be tolerable if we wanted to measure the cloud. Similarly, if the airplane flies through turbulence we would like to measure changes in air speed. Variations in temperature and humidity would be vital in the flight of a radiosonde, so again the time constant of the sensors would be considered. Fluxes of heat, water vapor, and momentum near the ground require fast sensors (with small time constants).
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Fleming, James Rodger. "Introduction." In First Woman. Oxford University Press, 2020. http://dx.doi.org/10.1093/oso/9780198862734.003.0001.

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Joanne Simpson transformed the science of the tropical atmosphere and set a course in science for professional women to follow. She had a lifelong passion for clouds and severe storms, flying into and above them, measuring and modeling them, theorizing about the role of tropical clouds in the planetary circulation, and mentoring a generation of tropical meteorologists. In 1993, just shy of her seventieth birthday, Joanne commandeered a fully equipped NASA-owned DC8 research airplane during a field project to study El Niño, and flew several flights directly into tropical cyclone Oliver in the Coral Sea, some 500 km off the coast of Townsville, Australia. She and the crew did this on several consecutive days. The aircraft was equipped with radar being tested for use on a new satellite to measure tropical rainfall, and they wanted to use it to collect the best possible data on storm structure and dynamics. The third flight, directly into the storm, pushed the plane to its limits. The excessive humidity and turbulent shaking shorted out the experimental electronics and rendered the plane unusable for future missions. NASA was not pleased. Buffeted but invigorated by the successful but totally unauthorized flights, Joanne told the press that she felt fortunate to have seen meteorology develop from the “horse-and-buggy era” to the space age....
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Conference papers on the topic "Airplanes Turbulence"

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Khamedov, Ruslan, Ruslan Baitlessov, and Luis Rojas-Solórzano. "CFD Study of Effects of Boundary Layer Suction on Transonic SC(2)-0714 Airfoil Performance." In ASME 2017 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/imece2017-70848.

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The complete understanding of the aerodynamics of wings and blades under transonic conditions represents a substantial challenge in the design of modern airplanes and turbomachinery. Transonic flow over airfoils may result in appearance of shock waves, which lead to increase in drag if not properly considered during the design stage. Therefore, it is a major challenge to design transonic airfoils such that potential appearance of shock waves is foreseen and negative drag effects are minimized. This paper presents the computational study of the SC(2)-0714 airfoil, focusing on its aerodynamics c
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Zur, Malte, Frank Otremba, Alexander Klippel, and Alfred Leder. "Numerical Simulation and Experimental Study of Cabin-Airflow and Transport of Gas-Mixtures in Aircraft Cargo Compartments: Model Validation." In 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 exp
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Vadake, Kshitij, and Jie Cui. "Numerical and Experimental Study of Turbulent Flows Around Clark Y-14 Aerofoil." In 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
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Granichin, Oleg, Tatjana Khantuleva, and Olga Granichina. "Local voting protocol for the adaptation of airplane's “feathers” in a turbulence flow." In 2017 American Control Conference (ACC). IEEE, 2017. http://dx.doi.org/10.23919/acc.2017.7963840.

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

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Miller, Teresa S., and Mark J. Moeller. "Wall Pressure Phase Velocity Measurements in a Turbulent Boundary Layer." In ASME 2012 Noise Control and Acoustics Division Conference at InterNoise 2012. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/ncad2012-0195.

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The turbulent boundary layer that forms on the outer surfaces of vehicles can be a significant source of interior noise. In automobiles this is known as wind noise, and at high speeds it dominates the interior noise. For airplanes the turbulent boundary is also a dominant noise source. Because of its importance as a noise source, it is desirable to have a model of the turbulent wall pressure fluctuations for interior noise prediction. One important parameter in building the wall pressure fluctuation model is the convection velocity. In this paper, the phase velocity was determined from the str
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Inglezakis, Dimitrios A., Georgios N. Lygidakis, and Ioannis K. Nikolos. "Flow Analysis of the M151 Aircraft Model Using the Academic CFD Code Galatea." In ASME 2017 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2017. http://dx.doi.org/10.1115/imece2017-70208.

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CFD (Computational Fluid Dynamics) solvers have become nowadays an integral part of the aerospace manufacturing process and product design, as their implementation allows for the prediction of the aerodynamic behavior of an aircraft in a relatively short period of time. Such an in-house academic solver, named Galatea, is used in this study for the prediction of the flow over the ARA (Aircraft Research Association) M151/1 aircraft model. The proposed node-centered finite-volume solver employs the RANS (Reynolds-Averaged Navier-Stokes) equations, combined with appropriate turbulence models, to a
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Perez, M., M. Ezzine, K. Billon, V. Clair, J. Mardjono, and M. Collet. "Design and Optimization of Piezoelectric Actuators for Aeroacoustic Noises Control in a Turbofan." In ASME 2020 Conference on Smart Materials, Adaptive Structures and Intelligent Systems. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/smasis2020-2436.

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Abstract This paper reports on the design and optimization of different types of piezoelectric actuators for aeroacoustic control applications. This study was carried out within the context of the European project CleanSky 2/InnoSTAT. The aim of our work is to reduce the aeroacoustic noises that appear in an airplane turbofan by adding an area of piezoelectric actuators on the Outlet Guide Vanes (OGV). These piezoelectric structures will subsequently be controlled with an active approach and tested in the open-jet anechoic wind tunnel at LMFE. The noise source which has to be reduce/control co
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Doh, Il, Il-Bum Kwon, Jiho Chang, and Sejong Chun. "Development of a Surface Flow Sensor for Measuring Turbulent Drag Force." In ASME-JSME-KSME 2019 8th Joint Fluids Engineering Conference. American Society of Mechanical Engineers, 2019. http://dx.doi.org/10.1115/ajkfluids2019-4680.

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Abstract A surface flow sensor is needed if turbulent drag force is to be measured over a vehicle, such as a car, a ship, and an airplane. In case of automobile industry, there are no automobile manufacturers which measure surface flow velocity over a car for wind tunnel testing. Instead, they rely on particle image velocimetry (PIV), pressure sensitive paint (PSP), laser Doppler anemometry (LDA), pitot tubes, and tufts to get information regarding the turbulent drag force. Surface flow sensors have not devised yet. This study aims at developing a surface flow sensor for measuring turbulent dr
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Obeid, Sohaib, Ratneshwar Jha, and Goodarz Ahmadi. "Closed-Loop Feedback Control of Flow Over a Flapped Airfoil at High Angles of Attack Using Identified NARMAX Model." In ASME 2012 Fluids Engineering Division Summer Meeting collocated with the ASME 2012 Heat Transfer Summer Conference and the ASME 2012 10th International Conference on Nanochannels, Microchannels, and Minichannels. American Society of Mechanical Engineers, 2012. http://dx.doi.org/10.1115/fedsm2012-72350.

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This study investigates closed-loop feedback control system design aimed at reduction of turbulent flow separation over a NACA 0015 airfoil having 30% integral type trailing edge flap and equipped with leading-edge and trailing edge synthetic jet actuators (SJAs). The multiple-input single-output controller employs system identification techniques based on Nonlinear Auto Regressive Moving Average with eXogenous inputs (NARMAX) method to model nonlinear dynamics of the flow. RANS FLUENT simulations for 2-D airfoil are used besides an analytical modeling for the set of synthetic actuators. The r
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