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Автор: Grafiati
Опубліковано: 6 вересня 2023

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Статті в журналах з теми "Wind tunnel cascade test"

1

Kiock, R., F. Lehthaus, N. C. Baines, and C. H. Sieverding. "The Transonic Flow Through a Plane Turbine Cascade as Measured in Four European Wind Tunnels." Journal of Engineering for Gas Turbines and Power 108, no. 2 (April 1, 1986): 277–84. http://dx.doi.org/10.1115/1.3239900.

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Reliable cascade data are esssential to the development of high-speed turbomachinery, but it has long been suspected that the tunnel environment influences the test results. This has now been investigated by testing one plane gas turbine rotor blade section in four European wind tunnels of different test sections and instrumentation. The Reynolds number of the transonic flow tests was Re2 = 8 × 105 based on exit flow conditions. The turbulence was not increased artificially. A comparison of results from blade pressure distributions and wake traverse measurements reveals the order of magnitude of tunnel effects.
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2

Rona, Aldo, Renato Paciorri, and Marco Geron. "Design and Testing of a Transonic Linear Cascade Tunnel With Optimized Slotted Walls." Journal of Turbomachinery 128, no. 1 (June 23, 2005): 23–34. http://dx.doi.org/10.1115/1.2101856.

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In linear cascade wind tunnel tests, a high level of pitchwise periodicity is desirable to reproduce the azimuthal periodicity in the stage of an axial compressor or turbine. Transonic tests in a cascade wind tunnel with open jet boundaries have been shown to suffer from spurious waves, reflected at the jet boundary, that compromise the flow periodicity in pitch. This problem can be tackled by placing at this boundary a slotted tailboard with a specific wall void ratio s and pitch angle α. The optimal value of the s-α pair depends on the test section geometry and on the tunnel running conditions. An inviscid two-dimensional numerical method has been developed to predict transonic linear cascade flows, with and without a tailboard, and quantify the nonperiodicity in the discharge. This method includes a new computational boundary condition to model the effects of the tailboard slots on the cascade interior flow. This method has been applied to a six-blade turbine nozzle cascade, transonically tested at the University of Leicester. The numerical results identified a specific slotted tailboard geometry, able to minimize the spurious reflected waves and regain some pitchwise flow periodicity. The wind tunnel open jet test section was redesigned accordingly. Pressure measurements at the cascade outlet and synchronous spark schlieren visualization of the test section, with and without the optimized slotted tailboard, have confirmed the gain in pitchwise periodicity predicted by the numerical model.
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3

Zhang, Jian Guo, and Hui Min Zhuang. "Wind Tunnel Test of Tall Buildings with Irregularities of Elevation." Applied Mechanics and Materials 578-579 (July 2014): 1208–11. http://dx.doi.org/10.4028/www.scientific.net/amm.578-579.1208.

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In this paper, 2 high-rise building models with ladder and cascade irregularities of elevation were tested in a wind tunnel respectively to measure the mean and fluctuating wind pressure distributions. The mean and RMS (root-mean-square) coefficients of the drag, lift and torsion moment on the measuring layer were obtained from the wind pressures. In the direction which the buildings were positive in the wind, the variation of these above mentioned coefficients with height and the power spectrum densities of the fluctuating wind loads on sudden changed positions were analyzed in detail. Compared with the elevation regular tall building, the wind load characteristics of irregular ones were more complicated.
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4

Borovkov, Aleksei. "Efficiency Analysis of Blade Cascades of Axial Compressors by the Results of Wind Tunnel Test." Journal of Advanced Research in Dynamical and Control Systems 12, no. 01-Special Issue (February 13, 2020): 953–61. http://dx.doi.org/10.5373/jardcs/v12sp1/20201146.

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5

Fořt, J., J. Fürst, J. Halama, V. Hric, P. Louda, M. Luxa, and D. Šimurda. "Numerical simulation of flow through cascade in wind tunnel test section and stand-alone configurations." Applied Mathematics and Computation 319 (February 2018): 633–46. http://dx.doi.org/10.1016/j.amc.2017.07.040.

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6

Hake, Leander, Felix Reinker, Robert Wagner, Stefan aus der Wiesche, and Markus Schatz. "The Profile Loss of Additive Manufactured Blades for Organic Rankine Cycle Turbines." International Journal of Turbomachinery, Propulsion and Power 7, no. 1 (March 21, 2022): 11. http://dx.doi.org/10.3390/ijtpp7010011.

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Results from an experimental profile loss study are presented of an additive manufactured linear turbine cascade placed in the test section of a closed-loop organic vapor wind tunnel. This test facility at Muenster University of Applied Sciences allows the investigation of high subsonic and transonic organic vapor flows under ORC turbine flow conditions at elevated pressure and temperature levels. An airfoil from the open literature was chosen for the cascade, and the organic vapor was Novec 649TM. Pitot probes measured the flow field upstream and downstream of the cascade. The inflow turbulence level was 0.5%. The roughness parameters of the metal-printed blades were determined, and the first set of flow measurements was performed. Then, the blade surfaces were further finished, and the impact of roughness on profile losses was assessed in the second flow measurement set. Although the Reynolds number level was relatively high, further surface treatment reduces the profile loss noticeably in organic vapor flows through the printed cascade.
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7

Niehuis, Reinhard, and Martin Bitter. "The High-Speed Cascade Wind Tunnel at the Bundeswehr University Munich after a Major Revision and Upgrade." International Journal of Turbomachinery, Propulsion and Power 6, no. 4 (October 29, 2021): 41. http://dx.doi.org/10.3390/ijtpp6040041.

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Since its first operation in 1956 at DFL Braunschweig and after its movement to Munich, the High-Speed Cascade Wind Tunnel (HGK) at Bundeswehr University Munich is intensively used for fundamental and application-oriented research on aero-thermodynamics of turbomachinery bladings. Numerous systematic airfoil design studies were performed over the last decades. Thanks to the HGK facility, which enables thorough and detailed cascade testing at turbomachinery-relevant conditions, many of those airfoils for different purposes finally made it into turbomachinery applications. Nowadays, the HGK still provides very useful contributions to the understanding of the complicated flow in compressor and turbine bladings, and thereby extends the knowledge on relevant physical phenomena. As a consequence of the intense usage, this unique test facility was subject to a major revision and upgrade. The performed changes are presented within this paper including an overview on new capabilities in terms of the extended operating range, the data acquisition system, and the recently available measurement equipment.
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8

Rechter, H., W. Steinert, and K. Lehmann. "Comparison of Controlled Diffusion Airfoils With Conventional NACA 65 Airfoils Developed for Stator Blade Application in a Multistage Axial Compressor." Journal of Engineering for Gas Turbines and Power 107, no. 2 (April 1, 1985): 494–98. http://dx.doi.org/10.1115/1.3239758.

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In their transonic cascade wind tunnel, DFVLR has done measurements on a conventional NACA 65, as well as on a controlled diffusion airfoil, designed for the same velocity triangle at supercritical inlet condition. These tested cascades represent the first stator hub section of a three-stage axial/one-stage radial combined compressor developed by MTU with the financial aid of the German Ministry of Research and Technology. One aspect of this project was the verification of the controlled diffusion concept for axial compressor blade design, in order to demonstrate the capabilities of some recent research results which are now available for industrial application. The stator blades of the axial compressor section were first designed using NACA 65 airfoils. In the second step, the controlled diffusion technique was applied for building a new stator set. Both stator configurations were tested in the MTU compressor test facility. Cascade and compressor tests revealed the superiority of the controlled diffusion airfoils for axial compressors. In comparison to the conventional NACA blades, the new blades obtained a higher efficiency. Furthermore, a closer matching of the compressor performance data to the design requirements was possible due to a more precise prediction of the turning angle.
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9

Tweedt, D. L., H. A. Schreiber, and H. Starken. "Experimental Investigation of the Performance of a Supersonic Compressor Cascade." Journal of Turbomachinery 110, no. 4 (October 1, 1988): 456–66. http://dx.doi.org/10.1115/1.3262219.

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Results are presented from an experimental investigation of a linear, supersonic compressor cascade tested in the supersonic cascade wind tunnel facility at the DFVLR in Cologne, Federal Republic of Germany. The cascade was derived from the near-tip section of a high-throughflow axial flow compressor rotor and has a design relative inlet Mach number of 1.61. Test data were obtained over the range of inlet Mach numbers from 1.30 to 1.17. Side-wall boundary layer suction was used to reduce secondary flow effects within the blade passages and to control the axial-velocity-density ratio (AVDR). Flow velocity measurements showing the wave pattern in the entrance region were obtained with a laser anemometer. The unique-incidence relationship for this cascade, relating the supersonic inlet Mach number to the inlet flow direction, is discussed. The influence of static pressure ratio and AVDR on the blade performance is described, and an empirical correlation is used to show the influence of these (independent) parameters for fixed inlet conditions on the exit flow direction and the total-pressure losses.
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10

Vlček, Václav, and Pavel Procházka. "Test section of the wind tunnel IT for aeroelastic experiments with blade cascades." EPJ Web of Conferences 213 (2019): 02095. http://dx.doi.org/10.1051/epjconf/201921302095.

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The article presents the way how the existing small vacuum aerodynamic tunnel IT (Institute of Thermomechanics) has been adapted for the measurement of the aeroelastic properties of the NACA 0015 airfoil and of the blade cascades composed of various types of blades with two degrees of freedom, pitch and common plunge. Attention was focused on the possibility of studying self-excited vibration at lower subsonic speeds. The modification of the test section is based on the knowledge gained during the study of self-excited airfoil oscillation.
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Дисертації з теми "Wind tunnel cascade test"

1

Baydar, Adem. "Hot-wire measurements of compressor blade wakes in a cascade wind tunnel/." Thesis, Monterey, California. Naval Postgraduate School, 1988. http://hdl.handle.net/10945/23254.

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A hot-wire system, with software designed for calibrating and taking data with single, double and triple hot-wire sensors separately, or three probes at once, was verified and used to make wake measurements downstream of a compressor stator blade in a cascade wind tunnel. Using a single hot-wire probe, velocity and turbulence data were obtained in the wake of the controlled-diffusion blade in order to verify LDV data taken in earlier studies. The tests were conducted at three inlet angles from near design incidence towards the expected stall condition at a Mach number of 0.25 and Reynolds number of about 700,000. Wake profiles were obtained from 0.08 to 0.2 chord lengths downstream of the blade. Good agreement was found with LDV measurements. Measurements at the highest incidence angle showed that the wake constituted one third of the flow and yet no separation occurred before the trailing edge on the suction side of the blade. Keywords: Laser doppler velocimeters
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2

Hamilton, Christianne Rhea. "Design of Test Sections for a High Enthalpy Wind Tunnel." MSSTATE, 2003. http://sun.library.msstate.edu/ETD-db/theses/available/etd-04082003-114126/.

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This document describes the design of a supersonic and a subsonic test section for a high enthalpy wind tunnel. A streamline is tracked through a supersonic test section using the method of characteristics. The specifics of the design program and the design techniques are illustrated for the supersonic section. The section of the paper dealing with the subsonic nozzle has a greatly diverse nature. This section details the inlet and exhaust restrictions and construction elements for the entire low speed system. The system is currently being set up for testing with the subsonic section, and the supersonic will eventually follow.
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3

Sparks, Russell. "A novel six degree of freedom dynamic wind tunnel test facility." Thesis, University of Manchester, 2008. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.492066.

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4

Murray, Kenneth Douglas. "Automation and extension of LDV measurements of off-design flow in a cascade wind tunnel." Thesis, Monterey, California. Naval Postgraduate School, 1989. http://hdl.handle.net/10945/25708.

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5

Tourn, Cremona Silvana Cecilia. "Characterization of a New Open Jet Wind Tunnel to Optimize and Test Vertical Axis Wind Turbines." Doctoral thesis, Universitat Rovira i Virgili, 2017. http://hdl.handle.net/10803/461079.

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Basat en el creixent interès en les tecnologies ambientals urbanes, l'estudi de turinas d'eix vertical de petita escala mostra desafiaments motivadors. En aquesta tesi, es presenten els criteris de disseny, les característiques i potencialitats d'un nou túnel de vent de secció de prova oberta. Té un àrea de sortida i la broquet del túnel de 1,5 x 1,5 m2, i es pot operar amb velocitats de sortida de 3 m / s a ​​17 m / s. La caracterització del flux s'ha dut a terme amb tubs pitot calibrats, anemòmetres de cassoletes i anemòmetres de fil calent. Es consideren dues configuracions diferents de l'àrea de prova, amb i sense sostre. Els mesuraments en el rang de velocitats de sortida disponibles mostren que la secció transversal, on les intensitats de velocitat i turbulència mostren un nivell acceptable d'uniformitat, té una àrea de 0,8 x 0,8 m2 i una dimensió de 2 m des de la sortida del broquet del túnel. En aquesta secció de treball, la intensitat màxima de la turbulència és del 4%. La caracterització detallada del flux realitzat indica que el túnel de vent es pot utilitzar per provar models a d'aerogeneradors de petita escala.
Basado en el creciente interés en las tecnologías ambientales urbanas, el estudio de turinas de eje vertical de pequeña escala muestra desafíos motivadores. En esta tesis, se presentan los criterios de diseño, las características y potencialidades de un nuevo túnel de viento de seccion de prueba abierta. Tiene un área de salida e la boquilla del túnel de 1,5 x 1,5 m2, y se puede operar con velocidades de salida de 3 m/s a 17 m/s. La caracterización del flujo se ha llevado a cabo con tubos pitot calibrados, anemómetros de cazoletas y anemómetros de hilo caliente. Se consideran dos configuraciones diferentes del área de prueba, con y sin techo. Las mediciones en el rango de velocidades de salida disponibles muestran que la sección transversal, donde las intensidades de velocidad y turbulencia muestran un nivel aceptable de uniformidad, tiene un área de 0,8 x 0,8 m2 y una dimensión de 2 m desde la salida de la boquilla del túnel. En esta sección de trabajo, la intensidad máxima de la turbulencia es del 4%. La caracterización detallada del flujo realizado indica que el túnel de viento se puede utilizar para probar modelos a de aerogeneradores de pequeña escala.
Based on the increasing interest in urban environmental technologies, the study of small scale vertical axis wind turbines shows motivating challenges. In this thesis, we present the design criteria, characteristics and potentials of a new open jet wind tunnel. It has a nozzle exit area of 1.5 x1.5 m2, and it can be operated with exit velocities from 3 m/s to 17 m/s. The characterization of the flow has been carried out with calibrated pitot tubes, cup anemometers, and hot wire anemometers. Two different configurations of the test area, with and without a ceiling, are considered. Measurements in the range of available exit velocities show that the cross section, where the velocity and turbulence intensities show an acceptable level of uniformity, has an area of 0.8 x 0.8 m2 and a streamwise dimension of 2 m from the nozzle exit of the tunnel. In this working section, the maximum turbulence intensity is 4%. The detailed characterization of the flow carried out indicates that the wind tunnel can be used to test small scale models of wind turbines.
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6

Dalley, Sam. "Wind tunnel measurements on a low rise building and comparison with full-scale." Thesis, University of Surrey, 1993. http://epubs.surrey.ac.uk/886/.

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7

Capasso, Michael Anthony. "Construction and wind tunnel test of a 1/12th scale helicopter model." Thesis, Monterey, Calif. : Springfield, Va. : Naval Postgraduate School ; Available from National Technical Information Service, 1994. http://handle.dtic.mil/100.2/ADA288487.

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8

Hamm, Christopher Eric. "AN ASSESSMENT OF FLOW QUALITY IN AN OPEN TEST SECTION WIND TUNNEL." MSSTATE, 2009. http://sun.library.msstate.edu/ETD-db/theses/available/etd-11022009-115210/.

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The subsonic wind tunnel facility at Mississippi State University has been converted to an open test section configuration. An experimental setup was developed which is easily configurable to allow for further research. Measurements of flow quality over select portions of the test section were made to attain a basic understanding of the performance of the new configuration. A program was developed in LabVIEW to control a 3-axis traverse and perform necessary data reduction. The traverse control program was developed to perform data acquisition using a hot-film probe to facilitate the necessary measurements. Data was gathered at two wind tunnel velocity settings over several test section locations. Results of the testing program yielded recommendations on the use of the open configuration. This paper documents the procedure and setup of the testing program to include discussion of the control/data acquisition program and a discussion of the findings and recommendations.
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9

James, Ralph William. "The effect of boundary layer blowing in the corner region of a linear compressor cascade wind tunnel." Thesis, This resource online, 1995. http://scholar.lib.vt.edu/theses/available/etd-05092009-040547/.

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10

Muthanna, Chittiappa. "The Effects of Free Stream Turbulence on the Flow Field through a Compressor Cascade." Diss., Virginia Tech, 2002. http://hdl.handle.net/10919/28753.

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The flow through a compressor cascade with tip leakage has been studied experimentally. The cascade of GE rotor B section blades had an inlet angle of 65.1º, a stagger angle of 56.9º, and a solidity of 1.08. The final turning angle of the cascade was 11.8º. This compressor configuration was representative of the core compressor of an aircraft engine. The cascade was operated with a tip gap of 1.65%, and operated at a Reynolds number based on the chord length (0.254 m) of 388,000. Measurements were made at 8 axial locations to reveal the structure of the flow as it evolved through the cascade. Measurements were also made to reveal the effects of grid generated turbulence on this flow. The data set is unique in that not only does it give a comparison of elevated free stream turbulence effects, but also documents the developing flow through the blade row of a compressor cascade with tip leakage. Measurements were made at a total of 8 locations 0.8, 0.23 axial chords upstream and 0, 0.27, 0.48, 0.77, 0.98, and 1.26 axial chords downstream of the leading edge of the blade row for both inflow turbulence cases. The measurements revealed the formation and development of the tip leakage vortex within the passage. The tip leakage vortex becomes apparent at approximately X/ca= 0.27 and dominated much of the endwall flow. The tip leakage vortex is characterized by high streamwise velocity deficits, high vorticity and high turbulence kinetic energy levels. The result showed that between 0.77 and 0.98 axial chords downstream of the leading edge, the vortex structure and behavior changes. The effects of grid generated turbulence were also documented. The results revealed significant effects on the flow field. The results showed a 4% decrease in the blade loading and a 20% reduction in the vorticity levels within tip leakage vortex. There was also a shift in the vortex path, showing a shift close to the suction side with grid generated turbulence, indicating the strength of the vortex was decreased. Circulation calculations showed this reduction, and also indicated that the tip leakage vortex increased in size by about 30%. The results revealed that overall, the turbulence kinetic energy levels in the tip leakage vortex were increased, with the most drastic change occurring at X/ca= 0.77.
Ph. D.
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Книги з теми "Wind tunnel cascade test"

1

Norris, R. B. The flying wind tunnel. New York: AIAA, 1989.

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2

B, Kelley P., and United States. National Aeronautics and Space Administration, eds. Wind tunnel test IA300 analysis and results. Huntsville, AL: Lockheed Missiles & Space Co., Huntsville Engineering Center, 1987.

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3

K, Wailes W., and Ames Research Center, eds. Advanced recovery systems wind tunnel test report. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1990.

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4

Keas, Paul. SOFIA II model telescope and wind tunnel test. [Moffett Field, Calif.]: NASA Ames Research Center, 1995.

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5

Baydar, Adem. Hot-wire measurements of compressor blade wakes in a cascade wind tunnel. Monterey, California: Naval Postgraduate School, 1988.

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6

Kelly, Abeyounis William, and Langley Research Center, eds. 16-foot transonic tunnel test section flowfield survey. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

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7

K, Abeyounis W., and Langley Research Center, eds. 16-foot transonic tunnel test section flowfield survey. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

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8

Kelly, Abeyounis William, and Langley Research Center, eds. 16-foot transonic tunnel test section flowfield survey. Hampton, Va: National Aeronautics and Space Administration, Langley Research Center, 1994.

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9

Ohman, L. H. New transonic test sections for the NAE 5ftx5ft trisonic wind tunnel. Ottawa: National Aeronautical Establishment, 1990.

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10

Randall, Peterson, and Ames Research Center, eds. Shake test results of the MDHC test stand in the 40- by 80-foot wind tunnel. Moffett Field, Calif: National Aeronautics and Space Administration, Ames Research Center, 1994.

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Частини книг з теми "Wind tunnel cascade test"

1

Gao, Lei. "Wind Tunnel Test." In Encyclopedia of Ocean Engineering, 1–4. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-10-6963-5_265-1.

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2

Gao, Lei. "Wind Tunnel Test." In Encyclopedia of Ocean Engineering, 2169–72. Singapore: Springer Nature Singapore, 2022. http://dx.doi.org/10.1007/978-981-10-6946-8_265.

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3

Chanetz, Bruno, Jean Délery, Patrick Gilliéron, Patrick Gnemmi, Erwin R. Gowree, and Philippe Perrier. "Computer-Aided Wind Tunnel Test and Analysis." In Springer Tracts in Mechanical Engineering, 273–83. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-35562-3_13.

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4

Lu, Zheng, Sami F. Masri, and Xilin Lu. "Wind Tunnel Test Study on Particle Damping Technology." In Particle Damping Technology Based Structural Control, 225–91. Singapore: Springer Singapore, 2020. http://dx.doi.org/10.1007/978-981-15-3499-7_7.

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5

Liu, Jin, Yuhui Song, and Jing Hu. "Investigation on Dynamic Derivative Test Technique in Hypersonic Wind Tunnel." In Lecture Notes in Electrical Engineering, 883–91. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_69.

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Yang, Lung-Jieh, Hsi-Chun Lee, Ai-Lien Feng, Chien-Wei Chen, Jenmu Wang, Yuan-Lung Lo, and Chia-Kuo Wang. "The Wind Tunnel Test and Unsteady CFD of an Ornithopter Formation." In Lecture Notes in Mechanical Engineering, 9–16. Singapore: Springer Singapore, 2016. http://dx.doi.org/10.1007/978-981-10-1771-1_4.

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7

Araszkiewicz, Piotr. "Use of Rapid Manufacturing Methods for Creating Wind Tunnel Test Models." In Lecture Notes in Mechanical Engineering, 36–43. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-04975-1_5.

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8

Gao, Liqiang, Xiong Hu, Dejian Sun, Ying Xi, and Guohua Wang. "Numerical Simulation and Wind Tunnel Test Validation of the Aerodynamic Brake Panel." In Advances in Mechanical Design, 911–21. Singapore: Springer Singapore, 2017. http://dx.doi.org/10.1007/978-981-10-6553-8_61.

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9

Hou, Yingyu, and Ziqiang Liu. "Aeroelastic Test of Large Flexible Structure Based on Electromagnetic Dry Wind Tunnel." In Lecture Notes in Electrical Engineering, 2684–91. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_215.

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10

Streit, Thomas, Heiko Geyr von Schweppenburg, David Cruz, and Rafael Sanchez. "DLR Feasibility Study of HLFC Wing Designs for S1MA Wind Tunnel Test." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design, 235–45. Cham: Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-79561-0_23.

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Тези доповідей конференцій з теми "Wind tunnel cascade test"

1

Kiock, R., F. Lehthaus, N. C. Baines, and C. H. Sieverding. "The Transonic Flow Through a Plane Turbine Cascade as Measured in Four European Wind Tunnels." In ASME 1985 Beijing International Gas Turbine Symposium and Exposition. American Society of Mechanical Engineers, 1985. http://dx.doi.org/10.1115/85-igt-44.

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Reliable cascade data are essential to the development of highspeed turbomachinery, but it has long been suspected that the tunnel environment influences the test results. This has now been investigated by testing one plane gas turbine rotor blade section in four European wind tunnels of different test sections and instrumentation. The Reynolds number of the transonic flow tests was Re2 = 8 · 105 based on exit flow conditions. The turbulence was not increased artificially. A comparison of results from blade pressure distributions and wake traverse measurements reveals the order of magnitude of tunnel effects.
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2

Wagner, Robert, Kai Dönnebrink, Felix Reinker, Karsten Hasselmann, Jonas Rejek, and Stefan aus der Wiesche. "A Modular Low-Speed Wind Tunnel With Two Test Sections and Variable Inflow Angle." In ASME 2015 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/imece2015-50232.

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A modular low-speed wind tunnel system was designed and developed. Due to the modular concept, the wind tunnel permitted open-jet operation, cascade testing or closed-circuit operation. The closed-circuit wind tunnel had two test sections, and it had a high quality test-section with variable flow angle that is particular valuable for airfoil or blade testing. Physical calibration of the wind tunnel facility validated the design rules and CFD methods used and demonstrated that these techniques can be employed successfully for future wind tunnel designs. A detailed study of the thermal behavior of the closed-circuit wind tunnel was conducted. A feedback control method based on a PI control law was developed and tested for the wind tunnel speed.
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3

Brunner, Stefan, Leonhard Fottner, and Heinz-Peter Schiffer. "Comparison of Two Highly Loaded Low Pressure Turbine Cascades Under the Influence of Wake-Induced Transition." In ASME Turbo Expo 2000: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/2000-gt-0268.

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Recent research has revealed positive effects of unsteady flow on the development of profile boundary layers in turbine cascades at conditions with a laminar suction side separation bubble. Compared to steady flow, a reduction of total pressure loss over a broad range of Reynolds-numbers has been shown. A new design of turbine blades with an increased blade loading (high lift) is possible if the effects of rotor-stator interaction are taken into account. With previous investigations at low speed cascade wind tunnels just one of the parameters Mach- or Reynolds-number could be adjusted during the tests. In order to verify the promising results gained at low speed cascade wind tunnels also at realistic Mach- and Reynolds-number combinations the present investigation has been carried out at the High Speed Cascade Wind Tunnel of the University of the Federal Armed Forces Munich. Being built inside a large pressure tank this high speed cascade wind tunnel offers the possibility to vary the Mach- and the Reynolds-number in the test section independently of each other in order to correctly simulate the flow conditions inside turbomachines. Thereby the experimental gap between investigations at low speed cascade wind tunnels and investigations at turbine-rig setups can be closed. In turbomachines, periodically unsteady flow is caused by the relative motion of rotor and stator rows. A wake generator has been designed and built in order to simulate a moving blade row upstream of a linear turbine cascade in the High Speed Cascade Wind Tunnel of the Universität der Bundeswehr München. The wakes are generated with cylindrical bars moving with a velocity of up to 40 m/s in the test section upstream of the cascade inlet plane. Measurements have been performed on two highly loaded low pressure turbine cascades (turbine cascade A and B) at varying Reynolds-numbers with steady and unsteady inlet flow conditions. For the unsteady inlet flow conditions, the frequency (Strouhal-number) of the wake passing has been altered by varying the speed of the bars. The turbulence intensity and the velocity deficit of the bar wakes have been measured with a 1D hot-wire probe. Wake-induced transition is qualitatively mapped out by employing a simultaneous surface hot-film anemometry system. Measurements of the surface pressure distribution and wake traverses have been performed. Due to an enlarged pitch to chord length ratio, turbine cascade B has a 15% larger lift than turbine cascade A, despite both having the same inlet and outlet conditions. Thereby the turbine cascades A and B have different airfoil shapes in order to take maximum advantage of the positive effects of rotor-stator interaction. Both cascades show a positive influence of unsteady inlet flow conditions to the boundary layer of the suction side, compared to steady inlet flow conditions, with respect of measured losses. With cascade A a maximum reduction of total pressure loss of 34% and with cascade B of 28% has been achieved, both compared to the appropriate steady inlet flow case. At design conditions of the turbine cascades (β1 = 135°, Ma2th = 0.7, Re2th = 100000) with unsteady inlet flow, both cascades have very similar low losses. Consequently, by taking into account the positive effects of wake-induced transition during the design process, new high lift blading with nearly the same low losses at unsteady inlet flow conditions could be achieved. This leads to a reduction of weight and cost of the whole turbine module for a constant stage loading.
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4

Munoz Lopez, Edwin J., Alexander Hergt, and Sebastian Grund. "The New Chapter of Transonic Compressor Cascade Design at the DLR." In ASME Turbo Expo 2022: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2022. http://dx.doi.org/10.1115/gt2022-80189.

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Abstract The approach to design compressor blades has been transformed over the years by the advent of efficient numerical optimization algorithms and increasing computing power. This has allowed designers to focus on finding the best optimization methodology for a desired application. However, transonic flow conditions on compressor blades still present considerable modeling and optimization challenges, making the optimization of even a 2D blade section a non-trivial undertaking. This paper then focuses on the design of a new state-of-the-art transonic compressor cascade for future wind tunnel test campaigns at the DLR. For this purpose, a thorough review was performed of similar cascades previously tested at the DLR’s Transonic Cascade Wind Tunnel. From this review, a main reference was picked corresponding to a modern cascade with notably good efficiency at high aerodynamic loading. The data gathered informed the definition of the optimization’s design strategy applied with the DLR’s in-house optimizer, AutoOpti. The process chain was evaluated with the DLR’s CFD solver for turbomachinery applications, TRACE, by performing RANS simulations with the k-ω SST turbulence model and γ-ReΘ transition model. The optimization was set to minimize two separate objective functions: the first one focused on the efficiency at the aerodynamic design point, while the second one was focused on the efficiency over the cascade’s working range. The result is a Pareto front of cascades with a wide variety of design characteristics and a considerable improvement in efficiency over the working range of about 24%. This improvement was achieved while maintaining a similar aerodynamic blade loading, quantified by a maximum increase of 3% of the de Haller number. Further post-optimization analyses were performed to select the “best” cascade for future wind tunnel test campaigns. The significant improvements obtained with respect to the reference and with a wide variety of cascade designs demonstrates that there is still much to be learned about blade design through optimization; even for 2D cascades and specially in transonic flow conditions.
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Graiff, Mattia, Marian Staggl, Emil Göttlich, and Christian Wakelam. "Design and Evaluation of a Flow Capturing Device for a High-Speed Wind Tunnel." In ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/gt2021-58667.

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Abstract Wind tunnel testing belongs to the most significant aspects of the technical development process. In order to improve the test environment conditions and open the possibility of closed loop operation, a flow capturing device is developed for a highspeed wind tunnel previously exhausting to ambient. The highspeed wind tunnel is used in conjunction with annular sector cascade test rigs to evaluate the performance of intermediate turbine ducts. In the presented paper, a modular design approach for the flow capturing device is presented; particular attention is reserved to optimal integration within the pre-existing test environment and to an efficient sealing strategy. Computational results provide the basis for the correct sizing of the device; the aerodynamic effects induced by the flow capturing device downstream of an annular sector cascade rig are shown to bear no influence on the quality of the test data. The presented results of several tests conducted under a wide range of conditions confirm the viability of the developed flow capturing device. The improvements to the pre-existing experimental setup achieved with the addition of the flow capturing device are furthermore presented in this paper, focusing on the obtained reduction in sound pressure and temperature level within the test facilities.
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Hasselmann, Karsten, Felix Reinker, Stefan aus der Wiesche, Eugeny Y. Kenig, Frithjof Dubberke, and Jadran Vrabec. "Performance Predictions of Axial Turbines for Organic Rankine Cycle (ORC) Applications Based on Measurements of the Flow Through Two-Dimensional Cascades of Blades." In ASME 2014 Power Conference. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/power2014-32098.

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The Organic-Rankine-Cycle (ORC) offers a great potential for waste heat recovery and use of low-temperature sources for power generation. However, the ORC thermal efficiency is limited by the relatively low temperature level, and it is, therefore, of major importance to design ORC components with high efficiencies and minimized losses. The use of organic fluids creates new challenges for turbine design, due to real-gas behavior and low speed of sound. The design and performance predictions for steam and gas turbines have been mainly based on measurements and numerical simulations of flow through two-dimensional cascades of blades. In case of ORC turbines and related fluids, such an approach requires the use of specially designed closed cascade wind tunnels. In this contribution, the specific loss mechanisms caused by the organic fluids are reviewed. The concept and design of an ORC cascade wind tunnel are presented. This closed wind tunnel can operate at higher pressure and temperature levels, and this allows for an investigation of typical organic fluids and their real-gas behavior. The choice of suitable test fluids is discussed based on the specific loss mechanisms in ORC turbine cascades. In future work, we are going to exploit large-eddy-simulation (LES) techniques for calculating flow separation and losses. For the validation of this approach and benchmarking different sub-grid models, experimental data of blade cascade tests are crucial. The testing facility is part of a large research project aiming at obtaining loss correlations for performance predictions of ORC turbines and processes, and it is supported by the German Ministry for Education and Research (BMBF).
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Sieverding, C. H., and T. Arts. "The VKI Compression Tube Annular Cascade Facility CT3." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-336.

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The purpose of this paper is to present the new transonic, annular facility developed at the von Karman Institute to investigate the aerodynamic heat transfer performances of real size advanced aero-engine and gas turbine components at correctly simulated operating conditions. The facility operates under the principle of an Isentropic Light Piston Compression Tube. Its definite advantage over classical blowdown wind tunnels is to independently model the freestream Mach and Reynolds numbers as well as the gas/wall/coolant temperature ratios. Its running time ranges between 0.1 and 1 s. The first part of the paper describes the design, the manufacturing and the installation of the different components of the wind tunnel and the test section. The second part deals with the different measurement techniques applied for aerodynamic and heat transfer measurements; it also describes some examples of the flow quality obtained in this new facility.
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Gonzalez, Carlos R., Guillaume F. Bidan, Jason W. Bitting, Christopher M. Foreman, Jean-Philippe Junca-Laplace, Kevin D. Wood, and Dimitris E. Nikitopoulos. "Design, Characterization, and Verification of a Closed Loop Wind Tunnel With Linear Cascade and Upstream Wake Generator." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-42999.

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A new cascade wind tunnel has been designed and constructed at the LSU Wind Tunnel Laboratory. The objective was to develop a versatile test facility, suitable for a wide range of experimental studies and measurements on turbine airfoils, especially with regards to film-cooling incorporating realistic unsteady effects due to passing wakes. The test section consists of a four passage linear cascade composed of three full blades and two shaped wall blades. The 2D blade shape profile of the cascade is a high-lift, low-pressure turbine L1A profile provided by the US Air Force Research Laboratories (AFRL), with a 152-mm axial chord. The Reynolds number based on the axial chord length at the nominal freestream velocity of 50 ms−1 is 500,000. A conveyor-based system was designed and fabricated to simulate the passing wakes of the upstream vanes (or blades) on the test blades (or vanes) depending on which airfoil types are put on the stationary frame and the moving frame of the conveyor. The original implementation uses blade profiles on the stationary frame and thick plate wake generators on the translating frame. Results are presented from hot-wire surveys conducted to characterize and qualify the velocity and turbulence intensity distributions and associated spectral characteristics at the cascade test section inlet, in the wake of the vanes and in the wake of the test blade. A blade instrumented with 123 pressure taps was used to acquire static pressure profiles of the cascade central blade, which were compared to the ones from the nominal airfoil design as well as to those obtained from a CFD simulation of the cascade flow. Incoming velocity and temperature profiles were found to be uniform to within a few percentage points, and the pressure coefficient distribution was found to be in good agreement with design values. The passage periodicity of the conveyor-belt-driven, flat-plates was verified and their wake was characterized. These results verified that the cascade wind tunnel operates according to design, thus proving to be a reliable test-bed for film cooling studies with and without unsteady wake effects. The design also incorporates an in-house-designed, miniature periscopic and adjustable laser sheet generating system integrated within the “dummy” blades to enable Particle Image Velocimetry measurements in the intra-blade domain.
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aus der Wiesche, Stefan, Felix Reinker, Robert Wagner, Leander Hake, and Max Passmann. "Critical and Choking Mach Numbers for Organic Vapor Flows Through Turbine Cascades." In ASME Turbo Expo 2021: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2021. http://dx.doi.org/10.1115/gt2021-59013.

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Abstract Results are presented of a theoretical and experimental study dealing with critical and choking Mach numbers of organic vapor flows through turbine cascades. A correlation was derived for predicting choking Mach numbers for organic vapor flows using an asymptotic series expansion valid for isentropic exponents close to unity. The theoretical prediction was tested employing a linear turbine cascade and a circular cylinder in a closed-loop organic vapor wind tunnel. The cascade was based on a classical transonic turbine airfoil for which perfect gas literature data were available. The cascade was manufactured by Selective Laser Melting (SLM), and a comparable low surface roughness level was established by subsequent surface finishing. Because the return of the closed-loop wind tunnel was equipped with an independent mass flow sensor and the test facility enabled stable long-term operation behavior, it was possible to obtain the choking Mach number with high accuracy. It was observed that non-perfect gas dynamics affect the critical Mach number locally, but the observed choking behavior of the turbine cascade was in good agreement with the asymptotic result for the considered dilute gas flow regime.
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Rona, A., and J. P. Gostelow. "Performance Margins of Non-Reflecting Slotted Walls in a Transonic Linear Cascade Tunnel." In ASME Turbo Expo 2006: Power for Land, Sea, and Air. ASMEDC, 2006. http://dx.doi.org/10.1115/gt2006-91057.

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An experimental investigation was conducted into the endwall interference from a low-pressure turbine nozzle blade profile tested in linear cascade at an isentropic discharge Mach number of 1.27. This was above the profile design point of Mach 0.995. This highlighted that inviscid flow phenomena, at the cascade pitchwise boundaries, are the main cause of spurious end-wall interference at these test conditions. Specifically, fish-tail shocks from the profile trailing edges reflect at these boundaries disturbing the interior flow. An appreciable reduction of such interference was obtained through the use of a slotted tailboard downstream of the outmost blade trailing edge, with void ratio and pitch optimized to operate at Mach 1.27 in this cascade wind tunnel. Cascade tests in the Mach number range 1.20 to 1.32 show that the tailboard at off-design conditions gives a more pitchwise periodic discharge than without a tailboard and a test section open jet boundary. Reducing the tailboard pitch from its design value of 64° to 62° does not further improve the flow pitchwise periodicity over the Mach number range 1.18 to 1.31. Over this range, the slotted tailboard at its design pitch angle retains an appreciable performance margin over the other two end-wall configurations tested.
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Звіти організацій з теми "Wind tunnel cascade test"

1

Lammert, Michael P., Kenneth J. Kelly, and Janet Yanowitz. Correlations of Platooning Track Test and Wind Tunnel Data. Office of Scientific and Technical Information (OSTI), February 2018. http://dx.doi.org/10.2172/1422885.

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2

Parker, M. J., and R. P. Addis. Wind tunnel test of Teledyne Geotech model 1564B cup anemometer. Office of Scientific and Technical Information (OSTI), April 1991. http://dx.doi.org/10.2172/5825677.

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3

Hand, M. M., D. A. Simms, L. J. Fingersh, D. W. Jager, J. R. Cotrell, S. Schreck, and S. M. Larwood. Unsteady Aerodynamics Experiment Phase VI: Wind Tunnel Test Configurations and Available Data Campaigns. Office of Scientific and Technical Information (OSTI), December 2001. http://dx.doi.org/10.2172/15000240.

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4

Steinle, Frank W., Booth Jr., Rhew Dennis, and Ray D. Determination of Anelastic-Induced Error in Wind Tunnel Test Force and Moment Measurements. Fort Belvoir, VA: Defense Technical Information Center, January 1999. http://dx.doi.org/10.21236/ada370968.

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Gillard, William J. Innovative Control Effectors (Configuration 101) Dynamic Wind Tunnel Test Report. Rotary Balance and Forced Oscillation Tests. Fort Belvoir, VA: Defense Technical Information Center, July 1998. http://dx.doi.org/10.21236/ada362903.

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6

Lau, Benton H., Nicole Obriecht, Tanner Gasow, Brandon Hagerty, Kelly C. Cheng, and Ben W. Sim. Boeing-SMART Rotor Wind Tunnel Test Data Report for DARPA Helicopter Quieting Program (HQP), Phase 1B. Fort Belvoir, VA: Defense Technical Information Center, September 2010. http://dx.doi.org/10.21236/ada532806.

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7

Clark, E. L. Error propagation equations and tables for estimating the uncertainty in high-speed wind tunnel test results. Office of Scientific and Technical Information (OSTI), August 1993. http://dx.doi.org/10.2172/10178382.

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8

Vocke, Robert III D., and Gerardo Nunez. Test Data Report, Low-Speed Wind Tunnel Drag Test of a 2/5 Scale Lockheed AH-56 Cheyenne Door-Hinge Hub. Fort Belvoir, VA: Defense Technical Information Center, July 2016. http://dx.doi.org/10.21236/ad1011994.

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9

Dodson, Michael G. An Historical and Applied Aerodynamic Study of the Wright Brothers' Wind Tunnel Test Program and Application to Successful Manned Flight. Fort Belvoir, VA: Defense Technical Information Center, May 2005. http://dx.doi.org/10.21236/ada437187.

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Yeager, William T., Noonan Jr., Singleton Kevin W., Wilbur Jeffrey D., and Matthew L. Performance and Vibratory Loads Data from a Wind-Tunnel Test of a Model Helicopter Main-Rotor Blade with a Paddle-Type Tip. Fort Belvoir, VA: Defense Technical Information Center, May 1997. http://dx.doi.org/10.21236/ada406400.

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