Relevant bibliographies by topics / Subsonic wind tunnels

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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 'Subsonic wind tunnels'

Author: Grafiati
Published: 4 June 2021
Last updated: 17 February 2022

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Journal articles on the topic "Subsonic wind tunnels"

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Tabatabaei, Narges, Ramis Örlü, Ricardo Vinuesa, and Philipp Schlatter. "Aerodynamic Free-Flight Conditions in Wind Tunnel Modelling through Reduced-Order Wall Inserts." Fluids 6, no. 8 (July 27, 2021): 265. http://dx.doi.org/10.3390/fluids6080265.

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Parallel sidewalls are the standard bounding walls in wind tunnels when making a wind tunnel model for free-flight condition. The consequence of confinement in wind tunnel tests, known as wall-interference, is one of the main sources of uncertainty in experimental aerodynamics, limiting the realizability of free-flight conditions. Although this has been an issue when designing transonic wind tunnels and/or in cases with large blockage ratios, even subsonic wind tunnels at low-blockage-ratios might require wall corrections if a good representation of free-flight conditions is intended. In order to avoid the cumbersome streamlining methods especially for subsonic wind tunnels, a sensitivity analysis is conducted in order to investigate the effect of inclined sidewalls as a reduced-order wall insert in the airfoil plane. This problem is investigated via Reynolds-averaged Navier–Stokes (RANS) simulations, and a NACA4412 wing at the angles of attack between 0 and 11 degrees at a moderate Reynolds number (400 k) is considered. The simulations are validated with well-resolved large-eddy simulation (LES) results and experimental wind tunnel data. Firstly, the wall-interference contribution in aerodynamic forces, as well as the local pressure coefficients, are assessed. Furthermore, the isolated effect of confinement is analyzed independent of the boundary-layer growth. Secondly, wall-alignment is modified as a calibration parameter in order to reduce wall-interference based on the aforementioned assessment. In the outlined method, we propose the use of linear inserts to account for the effect of wind tunnel walls, which are experimentally simple to realize. The use of these inserts in subsonic wind tunnels with moderate blockage ratio leads to very good agreement between free-flight and wind tunnel data, while this approach benefits from simple manufacturing and experimental realization.
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Wiriadidjaja, Surjatin, Fadilah Hasim, Shuhaimi Mansor, Waqar Asrar, Azmin Shakrine Mohd Rafie, and Ermira Junita Abdullah. "Subsonic Wind Tunnels in Malaysia: A Review." Applied Mechanics and Materials 225 (November 2012): 566–71. http://dx.doi.org/10.4028/www.scientific.net/amm.225.566.

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In Malaysia, there exist wind tunnels operated by several universities and organizations. Most of them are actively used for a variety of experimental works that are needed by uncounted educational curricula and aerodynamics related researches. Lately, wind tunnels have even become increasingly accepted as one of common engineering tools in solving of unexpected and abundant wind engineering problems that are continually facing automotive industries, oil and gas companies, as well as governmental agencies and ministries. This paper is meant to present an overview of the existing wind tunnels, accompanied with information on some important technical data, and added, to a lesser extent, with complementary information about backgrounds and design philosophies. The emphasis is, however, given only to those with test section size of 1.0 square meter or larger. From the general point of view, some information about testing capabilities and trends in wind tunnel technology is also presented.
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Hrúz, Michal, Pavol Pecho, and Martin Bugaj. "Design procedure and honeycomb screen implementation to the air transtport department’s subsonic wind tunnel." AEROjournal 16, no. 2 (2020): 3–8. http://dx.doi.org/10.26552/aer.c.2020.2.1.

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Wind tunnels are the most widely used tools when comes to validation of Reynold number. Most of wind tunnels use various air straighteners or flow conditioners to achieve as most unified air flow as it’s possible. This article deals with design and creation procedure of air flow straightener – honeycomb screen. Based on mathematical relations and empirical experience defines dimensions and characteristics for subsonic wind tunnel of the Air Transport Department of University of Žilina. Wind tunnel equipped with a suitable screen provides more relevant and accurate data, which are crucial for final validation of results of test objects.
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Wolf, T. "Improvement and modernization of subsonic wind tunnels." Journal of Aircraft 30, no. 1 (January 1993): 57–63. http://dx.doi.org/10.2514/3.46305.

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Krajček Nikolić, Karolina, Anita Domitrović, and Slobodan Janković. "Estimation of Aerodynamic Coefficients in a Small Subsonic Wind Tunnel." PROMET - Traffic&Transportation 30, no. 4 (September 10, 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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Wiriadidjaja, Surjatin, Azmin Shakrine Mohd Rafie, Fairuz Izzuddin Romli, and Omar Kassim Ariff. "Aerodynamic Interference Correction Methods Case: Subsonic Closed Wind Tunnels." Applied Mechanics and Materials 225 (November 2012): 60–66. http://dx.doi.org/10.4028/www.scientific.net/amm.225.60.

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The approach to problems of wall interference in wind tunnel testing is generally based on the so-called classical method, which covers the wall interference experienced by a simple small model or the neo-classical method that contains some improvements as such that it can be applied to larger models. Both methods are analytical techniques offering solutions of the subsonic potential equation of the wall interference flow field. Since an accurate description of wind tunnel test data is only possible if the wall interference phenomena are fully understood, uncounted subsequent efforts have been spent by many researchers to improve the limitation of the classical methods by applying new techniques and advanced methods. However, the problem of wall interference has remained a lasting concern to aerodynamicists and it continues to be a field of active research until the present. The main objective of this paper is to present an improved classical method of the wall interference assessment in rectangular subsonic wind tunnel with solid-walls.
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Ghorbanian, Kaveh, Mohammad Reza Soltani, and Mojtaba Dehghan Manshadi. "Experimental investigation on turbulence intensity reduction in subsonic wind tunnels." Aerospace Science and Technology 15, no. 2 (March 2011): 137–47. http://dx.doi.org/10.1016/j.ast.2010.06.009.

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Gorbushin, Anton Roaldovich. "AIR HUMIDITY EFFECT ON FLOW PARAMETERS IN SUBSONIC AND TRANSONIC WIND TUNNELS." TsAGI Science Journal 49, no. 1 (2018): 1–12. http://dx.doi.org/10.1615/tsagiscij.2018026783.

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Starikov, O. Yu. "The study of the induction of subsonic wind tunnels with an axisymmetric working part." Fluid Dynamics 20, no. 1 (1985): 130–33. http://dx.doi.org/10.1007/bf01097375.

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Meyer, O., W. Nitsche, and I. Futterer. "Numerical and experimental investigations on the reduction of wind tunnel wall interference by means of adaptive slots." Aeronautical Journal 105, no. 1052 (October 2001): 571–80. http://dx.doi.org/10.1017/s0001924000012513.

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Abstract The flow in many wind tunnel experiments is affected by the presence of test section walls. The resulting interference can be minimised by correcting the measured model pressures, or by influencing the model flow directly with the use of ventilated or adaptive test section walls. The objective behind the latter technique is to guide the flow in the test section to achieve low interference (i.e. free flow) condition at the model. The most successful technique of flexible, adaptive walls is still restricted to small research wind tunnels due to its mechanical complexity. However, a very promising alternative is the use of adaptive slots in the test section walls. This concept combines the method of passive slotted walls, as they are already implemented in many large wind tunnels, and flexible walls. Additionally, this technique presents the opportunity of full 3D adaptations because the slots can be situated in all four test section walls. This paper presents preliminary experimental results and the latest numerical calculations on the effectiveness of adaptive slots. The experiments were conducted under high subsonic flow conditions in the new slotted test section of the transonic wind tunnel at TU Berlin’s Aeronautical Institute (ILR). The numerical results presented are focussed on the 2D slot adaptation of a 2D-model (CAST7 aerofoil) and the 3D slot adaptation of a body of revolution (3D-ETB). In addition, basic studies were made of the flows associated with a single slot on one wall and a bump on the other. The numerical and the first experimental investigations have shown the potential of adaptive slots to reduce wall interferences effectively. The adaptation accuracy of the investigated slot configurations deviated not more than 3% from the reference case (2D-wall adaptation).
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Dissertations / Theses on the topic "Subsonic wind tunnels"

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Szleper, Michele Lee. "Converging nozzle design for a subsonic wind tunnel to test heat sinks under impinging and parallel airflows." Thesis, Georgia Institute of Technology, 2002. http://hdl.handle.net/1853/17124.

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Suratanakavikul, Varangrat. "Computational study of compressible flow in an S-shaped duct." Thesis, Imperial College London, 1999. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.313370.

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Pantaloni, Luigi. "Experimental analysis of the flow behind a probe rake in a high speed subsonic wind tunnel." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2013. http://amslaurea.unibo.it/4882/.

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Taylor, Nigel John. "Adaptive wall technology for two-dimensional wind tunnel testing at high subsonic through to low supersonic speeds." Thesis, University of Southampton, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.294622.

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Brundin, Desirée. "An Experimental Study of the High-Lift System and Wing-Body Junction Wake Flow Interference of the NASA Common Research Model." Thesis, KTH, Optimeringslära och systemteori, 2017. http://urn.kb.se/resolve?urn=urn:nbn:se:kth:diva-209242.

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This thesis investigates the turbulent flow in the wake of the wing-body junction of the NASA Common Research Model to further reveal its complex vortical structure and to contribute to the reference database used for Computational Fluid Dynamics validation activities. Compressible flows near two wall-boundary layers occurs not only at the wing-body junction but at every control surface of an airplane, therefore increased knowledge about this complex flow structure could potentially improve the estimates of drag performance and control surface efficiency, primarily for minimizing the environmental impact of commercial flight. The airplane model is modified by adding an inboard flap to investigate the influence from the deflection on the vorticity and velocity field. Future flap designs and settings are discussed from a performance improvement point of view, with the investigated flow influence in mind. The experimental measurements for this thesis were collected using a Cobra Probe, a dynamic multi-hole pressure probe, for Reynolds numbers close to one million based on the wing root chord. A pre-programmed three-dimensional grid was used to cover the most interesting parts of the junction flow. The facility used for the tests is a 120 cm by 80 cm indraft, subsonic wind tunnel at NASA Ames Research Center’s Fluid Mechanics Lab, which provides an on-set flow speed of around Mach 0.15, corresponding to approximately 48 m/s.
Den här avhandlingen undersöker det turbulenta flödet runt övergången mellan flygplanskropp och vinge på en NASA Common Research Model för att vidare utforska den komplexa, tredimensionella strukturen av flödet och bidra till NASA’s officiella databas för jämförelser med simulerade flöden. Kompressibla flöden nära tvåväggsgränsskikt uppkommer inte bara vid övergången mellan flygplanskropp och vinge utan även vid varje kontrollyta på ett flygplan. Ökad kunskap om flödets beteende vid sådana områden kan därför bidra till en bättre uppskattning av prestanda och effektivitet av kontrollytorna och flygplanet i sin helhet, vilket kan bidra till minskad miljöpåverkan från kommersiell flygtrafik. Flygplansmodellen är modifierad genom montering av en vingklaff på den inre delen av vingen, detta för att undersöka hur olika vinklar på klaffarnas nedböjning påverkar flödets struktur och hastighetsfält. Framtida klaffdesigner och inställningar för ökad prestanda diskuteras även utifrån denna påverkan. Mätningarna i vindtunneln gjordes med en Cobra Probe, ett dynamisk tryckmätningsinstrument, speciellt designad för turbulenta och instabila flöden. Reynoldsnumren som generades av den subsoniska, indrags-vindtunneln var ungefär en miljon baserad på vingrotens längd, vilket motsvarar knappt en tiondel av normala flygförhållanden för samma flygplansmodell.
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Tanner, Christopher Lee. "Aeroelastic analysis and testing of supersonic inflatable aerodynamic decelerators." Diss., Georgia Institute of Technology, 2012. http://hdl.handle.net/1853/47534.

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The current limits of supersonic parachute technology may constrain the ability to safely land future robotic assets on the surface of Mars. This constraint has led to a renewed interest in supersonic inflatable aerodynamic decelerator (IAD) technology, which offers performance advantages over the DGB parachute. Two supersonic IAD designs of interest include the isotensoid and tension cone, named for their respective formative structural theories. Although these concepts have been the subject of various tests and analyses in the 1960s, 1970s, and 2000s, significant work remains to advance supersonic IADs to a technology readiness level that will enable their use on future flight missions. In particular, a review of the literature revealed a deficiency in adequate aerodynamic and aeroelastic data for these two IAD configurations at transonic and subsonic speeds. The first portion of this research amended this deficiency by testing flexible IAD articles at relevant transonic and subsonic conditions. The data obtained from these tests showed that the tension cone has superior drag performance with respect to the isotensoid, but that the isotensoid may demonstrate more favorable aeroelastic qualities than the tension cone. Additionally, despite the best efforts in test article design, there remains ambiguity regarding the accuracy of the observed subscale behavior for flight scale IADs. Due to the expense and complexity of large-scale testing, computational fluid-structure interaction (FSI) analyses will play an increasingly significant role in qualifying flight scale IADs for mission readiness. The second portion of this research involved the verification and validation of finite element analysis (FEA) and computational fluid dynamic (CFD) codes for use within an FSI framework. These verification and validation exercises lend credence to subsequent coupled FSI analyses involving more complex geometries and models. The third portion of this research used this FSI framework to predict the static aeroelastic response of a tension cone IAD in supersonic flow. Computational models were constructed to mimic the wind tunnel test articles and flow conditions. Converged FSI responses computed for the tension cone agreed reasonably well with wind tunnel data when orthotropic material models were used and indicated that current material models may require unrealistic input parameters in order to recover realistic deformations. These FSI analyses are among the first results published that present an extensive comparison between FSI computational models and wind tunnel data for a supersonic IAD.
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(7038167), Claire S. Diffey. "Characterization of The Flow Quality in the Boeing Subsonic Wind Tunnel." Thesis, 2019.

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Good wind-tunnel flow quality characteristics are vital to using test data in the aerodynamic design process. Spatially uniform velocity profiles are required to avoid yaw and roll moments that would not be present in real flight conditions. Low turbulence intensity levels are also important as several aerodynamic properties are functions of turbulence intensity. When measuring mean flow and turbulence properties, hot-wire anemometry offers good spatial resolution and high-frequency response with a fairly simple operation, and the ability to make near-wall measurements. Using hot-wire anemometry, flow quality experiments were conducted
in a closed-circuit wind tunnel with a test section that has a cross section area of 1.2 m x 1.8 m (4 ft. x 6 ft.). The experiments included measurements of flow velocity and turbulence intensity variation over the test section cross-section, spatial and temporal temperature variation, and
boundary layer measurements. The centerline velocity and turbulence intensity were also measured for flow speeds ranging from 13 to 43 m/s.
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Books on the topic "Subsonic wind tunnels"

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Watmuff, J. H. Design of a new contraction for the ARL low speed wind tunnel (U). Melbourne, Australia: Aeronautical Research Laboratories, 1986.

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Gentry, Garl L. The Langley 14- by 22-foot subsonic tunnel: description, flow characteristics, and guide for users. Hampton, Va: Langley Research Center, 1990.

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Bowcutt, K. G. The use of panel methods for the development of low subsonic wall interference and blockage corrections. New York: AIAA, 1985.

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Johnson, William G. The 13-inch magnetic suspension and balance system wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1989.

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Johnson, William G. The 13-inch magnetic suspension and balance system wind tunnel. Hampton, Va: Langley Research Center, 1989.

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Johnson, William G. The 13-inch magnetic suspension and balance system wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1989.

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Johnson, William G. The 13-inch magnetic suspension and balance system wind tunnel. [Washington, DC]: National Aeronautics and Space Administration, Scientific and Technical Information Division, 1989.

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Manuel, Gregory S. Effect of collector configuration on test section turbulence levels in an open-jet wind tunnel. Hampton, Va: Langley Research Center, 1992.

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Frink, Neal T. Subsonic wind-tunnel measurements of a slender wind-body configuration employing a vortex flap. Hampton, Va: Langley Research Center, 1987.

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Orie, Nettie M. User's manual for the Langley Research Center 14- by 22-foot subsonic tunnel static data acquisition system. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1993.

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Book chapters on the topic "Subsonic wind tunnels"

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Chanetz, Bruno, Jean Délery, Patrick Gilliéron, Patrick Gnemmi, Erwin R. Gowree, and Philippe Perrier. "Subsonic Wind Tunnels." In Springer Tracts in Mechanical Engineering, 51–95. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-35562-3_3.

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Kirchheck, Daniel, Dominik Saile, and Ali Gülhan. "Rocket Wake Flow Interaction Testing in the Hot Plume Testing Facility (HPTF) Cologne." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 145–62. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-53847-7_9.

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Abstract Rocket wake flows were under investigation within the Collaborative Research Centre SFB/TRR40 since the year 2009. The current paper summarizes the work conducted during its third and final funding period from 2017 to 2020. During that phase, focus was laid on establishing a new test environment at the German Aerospace Center (DLR) Cologne in order to improve the similarity of experimental rocket wake flow–jet interaction testing by utilizing hydrogen–oxygen combustion implemented into the wind tunnel model. The new facility was characterized during tests with the rocket combustor model HOC1 in static environment. The tests were conducted under relevant operating conditions to demonstrate the design’s suitability. During the first wind tunnel tests, interaction of subsonic ambient flow at Mach 0.8 with a hot exhaust jet of approx. 920 K was compared to previously investigated cold plume interaction tests using pressurized air at ambient temperature. The comparison revealed significant differences in the dynamic response of the wake flow field on the different types of exhaust plume simulation.
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Verma, Neeraj, and Beena D. Baloni. "Calibration of Reference Velocity and Longitudinal Static Pressure Variation in the Test Section of an Open-Type Subsonic Wind Tunnel." In Advances in Applied Mechanical Engineering, 107–14. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-1201-8_12.

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"Recommended Practice: Calibration of Subsonic and Transonic Wind Tunnels (AIAA R-093-2003(2018))." In Recommended Practice: Calibration of Subsonic and Transonic Wind Tunnels (AIAA R-093-2003(2018)). Washington, DC: American Institute of Aeronautics and Astronautics, Inc., 2003. http://dx.doi.org/10.2514/4.476624.001.

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A., N. "Design Features of a Low Turbulence Return Circuit Subsonic Wind Tunnel Having Interchangeable Test Sections." In Wind Tunnel Designs and Their Diverse Engineering Applications. InTech, 2013. http://dx.doi.org/10.5772/52989.

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Georgiou, Georgia, Hamed Haddad Khodaparast, and Jonathan E. Cooper. "Uncertainty Quantification of Aeroelastic Stability." In Advances in Computational Intelligence and Robotics, 329–56. IGI Global, 2014. http://dx.doi.org/10.4018/978-1-4666-4991-0.ch016.

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The application of uncertainty analysis for the prediction of aeroelastic stability, using probabilistic and non-probabilistic methodologies, is considered in this chapter. Initially, a background to aeroelasticity and possible instabilities, in particular “flutter,” that can occur in aircraft is given along with the consideration of why Uncertainty Quantification (UQ) is becoming an important issue to the aerospace industry. The Polynomial Chaos Expansion method and the Fuzzy Analysis for UQ are then introduced and a range of different random and quasi-random sampling techniques as well as methods for surrogate modeling are discussed. The implementation of these methods is demonstrated for the prediction of the effects that variations in the structural mass, resembling variations in the fuel load, have on the aeroelastic behavior of the Semi-Span Super-Sonic Transport wind-tunnel model (S4T). A numerical model of the aircraft is investigated using an eigenvalue analysis and a series of linear flutter analyses for a range of subsonic and supersonic speeds. It is shown how the Probability Density Functions (PDF) of the resulting critical flutter speeds can be determined efficiently using both UQ approaches and how the membership functions of the aeroelastic system outputs can be obtained accurately using a Kriging predictor.
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Conference papers on the topic "Subsonic wind tunnels"

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Crites, R., and F. Steinle, r. "Wall interference reduction methods for subsonic wind tunnels." In 33rd Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-107.

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Lacey, John. "Concept for Reducing the Cost of Subsonic Wind Tunnels." In USAF Developmental Test and Evaluation Summit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2004. http://dx.doi.org/10.2514/6.2004-6828.

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Wolf, T., and T. Wolf. "Computation of power requirements for subsonic and transonic wind tunnels." In 15th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1997. http://dx.doi.org/10.2514/6.1997-2223.

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PASS, CLAY. "A wake blockage correction method for small subsonic wind tunnels." In 25th AIAA Aerospace Sciences Meeting. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-294.

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WOLF, T. "On the possibilities for improvement and modernization of subsonic wind tunnels." In 16th Aerodynamic Ground Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-1423.

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CROWDER, JAMES. "Infrared cameras for detection of boundary layer transition in transonic and subsonic wind tunnels." In 21st Fluid Dynamics, Plasma Dynamics and Lasers Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-1450.

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Marino, Antonello, and Aldo Bonfiglioli. "Optimization of the Porosity Distribution in Transonic Wind Tunnel." 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/fedsm2012-72487.

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During past years, to improve the quality of wind tunnel data in transonic configurations, researchers first designed new wind tunnel geometries (as porous and/or slotted wind tunnels), then developed more accurate correction laws giving acceptable results in certain conditions but absolutely not sufficient to satisfy the increasing aeronautical requirements. Recent studies showed that the quality of wind tunnel data can be improved by using test sections provided with variable streamwise porosity distributions instead of the typical uniform ones. Some authors identified this new concept of variable porosity distribution as the third generation of porous wind tunnels. In order to improve knowledge about effects of the porosity distribution on the wall interference in subsonic/transonic conditions, an experimental investigation was carried out in the PT-1 CIRA transonic wind tunnel in the Mach range between 0.3 and 0.9 (over 400 test points were measured on different models and wall porosity configurations). At this aim, a dedicated experimental setup consisting in five plates positioned on the top and bottom walls of the PT-1 porous test section, has been designed and realized. Setting independently each plate, it is possible to obtain practically unlimited combinations of porosity distributions along the streamwise direction. The final purpose of the present activity was to evaluate the optimal porosity distribution able to minimize wind tunnel wall interferences in the considered Mach range. The huge number of factors (Mach number and the positions of the five plates setting the porosity distribution) made practically impossible to study the porosity distribution effects by using a traditional One Factor At a Time (OFAT) approach. Therefore, the optimum porosity distribution has been achieved through an experiment designed with a Modern Design of Experiment (MDOE) approach. Within the MDOE approach, the RSM (Response Surface Modeling) has been selected. The objective of the experiment, designed with the RSM approach, is to acquire a sufficient number of data to create one or more response surface models to be used to predict the response variable of interest (within a specified uncertainty) as function of the factors which can affect the selected response variables. The best porosity distribution able to improve the quality of wind tunnel data has been found for the PT-1 Wind Tunnel (but results and/or the procedure are applicable to all similar Wind Tunnels). In the present paper, to contextualize the activity, after a short summary of the historical wind tunnel development, the stat of art of the variable streamwise porosity distribution is discussed. Then, the experimental setup to simulate in wind tunnel several streamwise variable porosity distribution and the design of Experiment are described. Finally, the main experimental results are reported and critically analyzed.
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Rueger, M., R. Crites, and R. Weirich. "Comparison of conventional and emerging ('measured variable') wall correction techniques for tactical aircraft in subsonic wind tunnels." In 33rd Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-108.

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Hoffman, Thomas, Albert Johns, and M. Bury. "Comparison of the 10x10 and the 8x6 Supersonic Wind Tunnels at the NASA Glenn Research Center for Low-Speed (Subsonic) Operation (Invited)." In 22nd AIAA Aerodynamic Measurement Technology and Ground Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2002. http://dx.doi.org/10.2514/6.2002-3246.

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MORT, K., P. SODERMAN, and L. MEYN. "OPTIMUM FULL-SCALE SUBSONIC WIND TUNNEL." In 14th Aerodynamic Testing Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-732.

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Reports on the topic "Subsonic wind tunnels"

1

Alexander, Michael G. Subsonic Wind Tunnel Testing Handbook. Fort Belvoir, VA: Defense Technical Information Center, May 1991. http://dx.doi.org/10.21236/ada240263.

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