Thematische Bibliographien / Wing test

Inhaltsverzeichnis

  1. Zeitschriftenartikel
  2. Dissertationen
  3. Bücher
  4. Buchteile
  5. Konferenzberichte
  6. Berichte der Organisationen

Auswahl der wissenschaftlichen Literatur zum Thema „Wing test“

Autor: Grafiati
Veröffentlicht am 28. Juni 2021
Zuletzt aktualisiert am 29. Juli 2025

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Zeitschriftenartikel zum Thema "Wing test"

1

Heryawan, Yudi, Hoon Cheol Park, Nam Seo Goo, Kwang Joon Yoon, and Yung Hwan Byun. "Structural Design, Manufacturing, and Wind Tunnel Test of a Small Expandable Wing." Key Engineering Materials 306-308 (March 2006): 1157–62. http://dx.doi.org/10.4028/www.scientific.net/kem.306-308.1157.

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This paper describes design, manufacturing, and wind tunnel test of a motor-driven small-scale expandable wing for MAV class vehicles. The bird-like expandable wing has been developed for investigating the influence of aspect ratio change on the lift and drag of the wing. As a typical bird wing, the wing is separated into inner and outer wings. The wing model consists of the linkage system made of carbon composite strip/rod and the remaining part covered with carbon composite sheet and multiple LIPCAs (Lightweight Piezo-Composite Actuators) mimicking wing feathers. The LIPCA actuator was used
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Siliang, Du, and Tang Zhengfei. "The Aerodynamic Behavioral Study of Tandem Fan Wing Configuration." International Journal of Aerospace Engineering 2018 (October 30, 2018): 1–14. http://dx.doi.org/10.1155/2018/1594570.

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The fan wing aircraft is a new concept based on a new principle, especially its wing which is based on a unique aerodynamic principle. A fan wing can simultaneously generate lift and thrust. In order to further improve its aerodynamic characteristics without changing its basic geometric parameters, two fan wings are installed along the longitudinal body, which is the composition of a tandem fan wing aircraft. Through numerical simulation, the lift and thrust of the fan wings were calculated with the distance, height, and installation angle of the front and rear fan wings changed, and the aerod
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Teo, Z. W., T. H. New, Shiya Li, T. Pfeiffer, B. Nagel, and V. Gollnick. "Wind tunnel testing of additive manufactured aircraft components." Rapid Prototyping Journal 24, no. 5 (2018): 886–93. http://dx.doi.org/10.1108/rpj-06-2016-0103.

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Purpose This paper aims to report on the physical distortions associated with the use of additive manufactured components for wind tunnel testing and procedures adopted to correct for them. Design/methodology/approach Wings of a joined-wing test aircraft configuration were fabricated with additive manufacturing and tested in a subsonic closed-loop wind tunnel. Wing deflections were observed during testing and quantified using image-processing procedures. These quantified deflections were then incorporated into numerical simulations and results had agreed with wind tunnel measurement results. F
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Zhang, Xitong, Gui Cheng, and Gang Chen. "A New Type Bionic Foldable Wing Design for High Maneuverable Unmanned Aerial Vehicle." Applied Sciences 13, no. 14 (2023): 8345. http://dx.doi.org/10.3390/app13148345.

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With the improvement of aircraft requirements in civil and military fields, aircraft are developing towards the direction of high efficiency and multi-mission. Foldable wing aircraft with large deformation capability will be able to meet flight requirements and performance under different conditions. Based on the bionic design concept, a feather-like foldable morphing wing based on a multi-link mechanism from the flight characteristics of birds was designed. In order to validate the feasibility of the proposed morphing wing conception, a UAV with bionic foldable wings was fabricated. The aerod
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Tsushima, Natsuki, Kenichi Saitoh, Hitoshi Arizono, and Kazuyuki Nakakita. "Structural and Aeroelastic Studies of Wing Model with Metal Additive Manufacturing for Transonic Wind Tunnel Test by NACA 0008 Example." Aerospace 8, no. 8 (2021): 200. http://dx.doi.org/10.3390/aerospace8080200.

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Additive manufacturing (AM) technology has a potential to improve manufacturing costs and may help to achieve high-performance aerospace structures. One of the application candidates would be a wind tunnel wing model. A wing tunnel model requires sophisticated designs and precise fabrications for accurate experiments, which frequently increase manufacturing costs. A flutter wind tunnel testing, especially, requires a significant cost due to strict requirements in terms of structural and aeroelastic characteristics avoiding structural failures and producing a flutter within the wind tunnel test
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Rogalla, Svana, Liliana D'Alba, Ann Verdoodt, and Matthew D. Shawkey. "Hot wings: thermal impacts of wing coloration on surface temperature during bird flight." Journal of The Royal Society Interface 16, no. 156 (2019): 20190032. http://dx.doi.org/10.1098/rsif.2019.0032.

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Recent studies on bird flight propose that hotter wing surfaces reduce skin friction drag, thereby improving flight efficiency (lift-to-drag ratio). Darker wings may in turn heat up faster under solar radiation than lighter wings. We used three methods to test the impact of colour on wing surface temperature. First, we modelled surface temperature based on reflectance measurements. Second, we used thermal imaging on live ospreys ( Pandion haliaetus ) to examine surface temperature changes with increasing solar irradiance. Third, we experimentally heated differently coloured wings in a wind tun
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Yao, Zhuoer, Zi Kan, and Daochun Li. "Gust Response of Spanwise Morphing Wing by Simulation and Wind Tunnel Testing." Aerospace 10, no. 4 (2023): 328. http://dx.doi.org/10.3390/aerospace10040328.

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The spanwise morphing wing can change its aerodynamic shape to suit its flight environment, thereby having the potential to improve the flight performance of the aircraft, especially in gusty conditions. To investigate the potential of morphing wings, the aerodynamic performance of a spanwise morphing wing with a flapping wingtip in a gust environment was analyzed in this paper. The aerodynamic characteristics of the morphing wing are hard to measure accurately, and thus a wind tunnel test was carried out to study the influences of morphing parameters, such as the morphing length, amplitude an
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Wijiatmoko, Gunawan, Eflita Yohana, Mohammad Tauviqirrahman, and Ivransa Zuhdi Pane. "Wind Tunnel Test on an Airplane Model with Cylindrical VGs attached on the Wing’s Upper Surface." E3S Web of Conferences 576 (2024): 01001. http://dx.doi.org/10.1051/e3sconf/202457601001.

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In aerodynamics, there is a lot of research regarding the implementation of vortex generators (VGs) which are placed in certain parts of aircraft to improve aerodynamic performance. Most of the previous study was carried out computationally using CFD software, while the VGs placement part was an airfoil shape only. This research aims to determine the effect of placing cylindrical VGs on the upper surface of the right and left wings of an airplane aerodynamic model, referring to the chord percentage from the leading edge. Apart from that, the effect of placing VGs along 1/3 of the wing length a
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O., Abdussalam, Fatimah, Abiaziem, Chioma V., and Makanjuola, John O. "Extraction And Evaluation Of Antidotes From Musca Domestica (Houseflies) Wings Against Its Body Pathogens." IOSR Journal of Environmental Science Toxicology and Food Technology 19, no. 1 (2025): 31–39. https://doi.org/10.9790/2402-1901013139.

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Musca domestica is an important insect vector of various myriads of microbes ranging from bacteria, fungi and parasites. They tend to infest food and drinks of human and animals causing severe diseases. Unfortunately, some of the microbes/diseases transmitted by this vector have developed resistance against various drugs (Drug Resistance Microbes). This current study evaluates the microbial loads on various body parts (Right wing, Left wing and Body Surface) of M. domestica captured from different locations in Ilaro, Ogun State and the antimicrobial properties of the body parts. One hundred an
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Khaghaninia, S., S. Mohammadi, A. Srafrazi, K. Nejad, and R. Zahiri. "Geometric Morphometric Study on Geographic Dimorphism of Coding Moth Cydia Pomonella (Lepidoptera, Tortricidae) from North West of Iran." Vestnik Zoologii 45, no. 5 (2011): e-20-e-28. http://dx.doi.org/10.2478/v10058-011-0028-z.

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Geometric Morphometric Study on Geographic Dimorphism of Coding MothCydia Pomonella(Lepidoptera, Tortricidae) from North West of IranDuring years 2003-2004, nine geographical populations of codling moth Cydia pomonella (Linnaeus) from 4 north western provinces of Iran were collected. By preparing 575 images from fore wings and 564 from hind wings, a total of 15 and 11 landmarks were determined for fore and hind wings, respectively. With transforming of landmark's geometrical data into partial warp scores, 26 and 18 scores were obtained for fore and hind wings, respectively. Canonical correlati
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Dissertationen zum Thema "Wing test"

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Dwyer, William P. (William Patrick). "Measurement of flow boundary condition data and wing pressures in a wind tunnel test of a 45 deg swept wing." Thesis, Massachusetts Institute of Technology, 1990. http://hdl.handle.net/1721.1/42182.

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Westin, Michelle Fernandino. "Aeroelastic modeling and experimental analysis of a flexible wing for wind tunnel flutter test." Instituto Tecnológico de Aeronáutica, 2010. http://www.bd.bibl.ita.br/tde_busca/arquivo.php?codArquivo=1121.

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The objective of this work is to investigate the flutter phenomena experimentally, which will unify high aspect ratio wings design for wind tunnel flutter tests (Dowell and Tang, 2002), cheaper aeroelastic models construction and a procedure used by Sheta, Harrand, Thompson and Strganac (2002) to identify the flutter onset power spectral density versus the frequency. Initially, an experimental model developed by Dowell and Tang (2002) has been considered as a baseline model and, from this point, two new models with different wing configurations were determined, including the slender body at wi
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Groenewald, Stephanus. "Development of a rotary-wing test bed for autonomous flight." Thesis, Stellenbosch : University of Stellenbosch, 2006. http://hdl.handle.net/10019.1/2814.

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Thesis (MScEng (Electrical and Electronic Engineering))--University of Stellenbosch, 2006.<br>This project developed a low-cost avionics system for a miniature helicopter to be used for research in the field of autonomous flight (UAVs). Previous work was done on a small, electrically powered helicopter with some success, but the overall conclusion was that the vehicle was underpowered. A new vehicle, the Miniature Aircraft X−Cell, was chosen for its ability to lift a larger payload, and previous work done with it by a number of other institutions. An expandable architecture was designed
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Eger, Charles Alfred Gaitan. "Design of a Scaled Flight Test Vehicle Including Linear Aeroelastic Effects." Thesis, Virginia Tech, 2013. http://hdl.handle.net/10919/23088.

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A procedure for the design of a scaled aircraft using linear aeroelastic scaling is developed and demonstrated. Previous work has shown the viability in matching scaled structural frequencies and mode shapes in order to achieve consistent linear scaling of simple models. This methodology is adopted for use on a high fidelity joined-wing aircraft model. Natural frequencies and mode shapes are matched by optimizing structural ply properties and nonstructural mass. A full-scale SensorCraft concept developed by AFRL and Boeing serves as the target model, and a 1/9th span geometrically scaled remot
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Smith, Todd J. "Development, Design, Manufacture and Test of Flapping Wing Micro Aerial Vehicles." Wright State University / OhioLINK, 2016. http://rave.ohiolink.edu/etdc/view?acc_num=wright1484659431737526.

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Zientarski, Lauren Ann. "Wind Tunnel Testing of a Variable Camber Compliant Wing with a Unique Dual Load Cell Test Fixture." University of Dayton / OhioLINK, 2015. http://rave.ohiolink.edu/etdc/view?acc_num=dayton1448893315.

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Garnand-Royo, Jeffrey Samuel. "Design and Evaluation of Geometric Nonlinearities using Joined-Wing SensorCraft Flight Test Article." Thesis, Virginia Tech, 2013. http://hdl.handle.net/10919/23234.

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The Boeing Joined-Wing SenorCraft is a novel aircraft design that has many potential benefits, especially for surveillance missions. However, computational studies have shown the potential for nonlinear structural responses in the joined-wing configuration due to aerodynamic loading that could result in aft wing buckling. The design, construction, and flight testing of a 1/9th scale, aeroelastically tuned model of the Joined-Wing SensorCraft has been the subject of an ongoing international collaboration aimed at experimentally demonstrating the nonlinear aeroelastic response in flight. To accu
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Brooks, W. G. "The design, construction and test of a postbuckled, carbon fibre reinforced plastic wing box." Thesis, Cranfield University, 1987. http://hdl.handle.net/1826/3292.

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A postbuckled, carbon fibre reinforced plastic (CFRP) wing box has been designed, manufactured and tested for an aerobatic light aircraft, the Cranfield Al. Methods of analysis have been evaluated including: i) Non-linear finite element analysis for the prediction o-f panel postbuckling. ii) A simpler technique based on an effective width method. This forms the core of a design program, 'oPTIMIST'. It predicts buckling loads, postbuckled reduced stiffness and overall column failure of co-cured hat stiffened panels. It then optimises the con-Figuration of a box beam for minimum weight. iii) The
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Di, Nicola Federico. "Energy harvesting from piezoelectric devices embedded in a 3D printed wing." Master's thesis, Alma Mater Studiorum - Università di Bologna, 2015. http://amslaurea.unibo.it/9705/.

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This thesis work has been carried out at Clarkson University in Potsdam NY, USA and involved the design of a low elongation wing, consisting of parts made by polylactide (PLA) using the fused deposition model (FDM) technology of Rapid Prototyping, then assembled together in a thin aluminum spar. The aim of the research is to evaluate the feasibility of collecting electrical energy by converting mechanical energy from the vibration of the wing flutter. With this aim piezoelectric stripes were glued in the inner part of the wing, as well as on the aluminum spar, as monomorphic configuration. Du
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Aarons, Tyler David. "Development and Implementation of a Flight Test Program for a Geometrically Scaled Joined Wing SensorCraft Remotely Piloted Vehicle." Thesis, Virginia Tech, 2011. http://hdl.handle.net/10919/36383.

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The development and implementation of a flight test program for an unmanned aircraft is a multidisciplinary challenge. This thesis presents the development and implementation of a rigorous test program for the flight test of a Geometrically Scaled Joined Wing SensorCraft Remotely Piloted Vehicle from concept through successful flight test. The design methodology utilized in the development of the test program is presented, along with the extensive formal review process required for the approval of the test plan by the Air Force Research Laboratory. The design, development and calibration of a
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Bücher zum Thema "Wing test"

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E, Walker Charlotte, and Langley Research Center, eds. Computational test cases for a rectangular supercritical wing undergoing pitching oscillations. National Aeronautics and Space Administration, Langley Research Center, 1999.

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A, Kennelly Robert, and Ames Research Center, eds. Transonic wind tunnel test of a 14% thick oblique wing. National Aeronautics and Space Administration, Ames Research Center, 1990.

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Goodyer, M. J. A swept wing panel in a low speed flexible walled test section. National Aeronautics and Space Administration, Scientific and Technical Information Division, 1988.

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Goodyer, M. J. A swept wing panel in a low speed flexible walled test section. Langley Research Center, 1987.

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C, Wilson John. Wind tunnel test results of a 1/8-scale fan-in-wing model. National Aeronautics and Space Administration, Langley Research Center, 1996.

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Phelps, Arthur E. Description of the U.S. Army small-scale 2-meter rotor test system. Langley Research Center, 1987.

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Center, Langley Research, ed. Low speed wind tunnel test of a propulsive wing/canard concept in the STOL configuration. National Aeronautics and Space Administration, Langley Research Center, 1987.

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L, Lawing Pierce, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. High-Reynolds-number test of a 5-percent-thick low-aspect-ratio semispan wing in the Langley 0.3-meter transonic cryogenic tunnel, wing tunnel distributions. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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L, Lawing Pierce, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. High-Reynolds-number test of a 5-percent-thick low-aspect-ratio semispan wing in the Langley 0.3-meter transonic cryogenic tunnel, wing tunnel distributions. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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L, Lawing Pierce, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Division., eds. High-Reynolds-number test of a 5-percent-thick low-aspect-ratio semispan wing in the Langley 0.3-meter transonic cryogenic tunnel, wing tunnel distributions. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1990.

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Buchteile zum Thema "Wing test"

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Petrocchi, Andrea, Rene Steijl, and George N. Barakos. "Numerical Study of Unsteady Shock/Boundary Layer Interaction." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer Nature Switzerland, 2025. https://doi.org/10.1007/978-3-031-86605-0_10.

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Abstract The present work investigates the ability of the Partially-Averaged Navier-Stokes (PANS) method to reproduce transonic buffet, occurring on airfoils and wings at transonic regime under specific flow conditions. The designed test case for this analysis is the OAT15A unswept wing at Mach number $$\text {M}_{\infty }=0.73$$ M ∞ = 0.73 and Reynolds number $$\text {Re}_c=3\times 10^6$$ Re c = 3 × 10 6 . The three-dimensional flow is studied by accounting for the wind tunnel walls in the experiments of Jacquin et al. [1]. The computations on a large-span, confined configuration revealed a s
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Liu, Jihai, Yingsong Gu, Ke Xie, and Pengtao Shi. "Flutter Modeling, Analysis and Test for Blended-Wing-Body Flying Wing." In Lecture Notes in Electrical Engineering. Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_78.

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Bo, Xiaoli. "Experimental Study on the Impact of Thermal Stress on Aircraft Structural Performance." In Lecture Notes in Mechanical Engineering. Springer Nature Singapore, 2024. http://dx.doi.org/10.1007/978-981-97-1876-4_101.

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AbstractThe local heat source of a civil aircraft affects the temperature of the lower panel structure of the center wing. In this paper, a local heat source is arranged on the lower panel structure of the center wing. The strain of the center wing lower panel skin under different temperature gradients under local thermal loads and the corresponding temperature gradients around the heat source were investigated. The natural mesh model and the fine finite element model were used to analyze the thermal load of the center wing lower panel. The temperature on the node was applied according to the
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Fu, Zhichao, and Ziqiang Liu. "Nonlinear Flutter Test of a Very Flexible Wing." In Lecture Notes in Electrical Engineering. Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_211.

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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. Springer International Publishing, 2021. http://dx.doi.org/10.1007/978-3-030-79561-0_23.

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Heryawan, Yudi, Hoon Cheol Park, Nam Seo Goo, Kwang Joon Yoon, and Yung Hwan Byun. "Structural Design, Manufacturing, and Wind Tunnel Test of a Small Expandable Wing." In Fracture and Strength of Solids VI. Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/0-87849-989-x.1157.

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Xu, Yuntao, Yi Liu, Zhigang Wu, and Chao Yang. "Investigation and Wind Tunnel Test on Gust Load Alleviation for a Flying Wing." In Lecture Notes in Mechanical Engineering. Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-99-8867-9_52.

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Zárate, José, and Hartmut Witte. "Design and Control of a Flapping Wing System Test Bench." In Advances in Service and Industrial Robotics. Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-19648-6_5.

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Reju, R., Sanoj P. Suresh, and R. Sabarishwaran. "Windtunnel Test of Co-Flow Jet Wing for Lift Enhancement." In Lecture Notes in Mechanical Engineering. Springer Nature Singapore, 2023. http://dx.doi.org/10.1007/978-981-19-7055-9_35.

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Yang, Yunjie, Saite Zhang, Xiangyang Wang, et al. "Wind Tunnel Free Flight Test on Attitude Control Strategy of the Flying-Wing Aircraft." In Lecture Notes in Electrical Engineering. Springer Nature Singapore, 2025. https://doi.org/10.1007/978-981-96-2268-9_40.

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Konferenzberichte zum Thema "Wing test"

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Costa, Guillermo, Sandilya Kambampati, Samuel Johnson, and Edward Smith. "Design, Fabrication, Test, and Evaluation of Small-Scale Tiltrotor Whirl Flutter Wind Tunnel Models." In Vertical Flight Society 71st Annual Forum & Technology Display. The Vertical Flight Society, 2015. http://dx.doi.org/10.4050/f-0071-2015-10286.

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Three generations of small, semispan, subscale tiltrotor wind tunnel models were designed, fabricated, and wind tunnel tested. The goal of this project was to develop a series of flutter tests at small scale and low cost that would experimentally validate a series of analytical models developed in-house; this required a wind tunnel model that had as low a flutter speed as was feasible, in order to permit it to be tested to the point of instability within the operating limits of the current facility. The first-generation model consisted of a hollow plastic wing rapid-prototyped from ABS plastic
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Colamartino, Ivan, Andrea Renzo, Marco Anghileri, and Fabrizio Turconi. "Full-scale crash test of the AW609 wing." In Vertical Flight Society 80th Annual Forum & Technology Display. The Vertical Flight Society, 2024. http://dx.doi.org/10.4050/f-0080-2024-1222.

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The AW609 tiltrotor features a unique high-mounted wing with rotatable nacelles positioned at the wing tips, it is capable of operating both in airplane and vertical flight mode. To achieve suited protection of the occupants during emergency landing, the wing - which is particularly stiff in order to sustain the heavy weights at the tips, where rotors, engines and transmissions are positioned - implements a controlled failure mechanism at root, so that during emergency landings it breaks and unloads the fuselage of the weight of wingbox and nacelles, thus avoiding catastrophic collapse. As the
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Hoff, Stefan, Federico Fonte, Keith Soal, Kees Kapteijn, and Oliver Schneider. "Whirl Flutter Testing of ATTILA Tiltrotor Testbed - Initial Results." In Vertical Flight Society 80th Annual Forum & Technology Display. The Vertical Flight Society, 2024. http://dx.doi.org/10.4050/f-0080-2024-1117.

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This paper presents the preliminary results of the recent whirl flutter wind tunnel test campaign performed within the Advanced Testbed for TILtrotor Aeroelastics (ATTILA) project. The Froude-scale ATTILA testbed consists of a semi-span wing with powered tip-mounted proprotor reflecting the proprietary design of the Next Generation Civil TiltRotor (NGCTR). An overview of the ATTILA testbed, wind tunnel test procedures, team organisation and preliminary flutter results are presented. In line with pre-entry dynamic characterization tests, the wind-on test activities in the DNW Large Low-speed Fa
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Abhishek, Abhishek, M. Krishna, Sourav Sinha, Joydeep Bhowmik, and Debopam Das. "Design, Development and Flight Testing of a Novel Quadrotor Convertiplane Unmanned Air Vehicle." In Vertical Flight Society 73rd Annual Forum & Technology Display. The Vertical Flight Society, 2017. http://dx.doi.org/10.4050/f-0073-2017-12294.

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This paper describes the design, development and flight testing of a small novel quadrotor convertiplane Unmanned Air Vehicle (UAV) which has four propellers driven by individual brushless DC motors mounted at the tip of tandem wings. The segment of the wing under the propeller downwash is tilted with the propeller to improve the hovering efficiency of the UAV. Tandem low and high wing design is chosen to mitigate the interference losses due to the influence of fore wing and propeller downwash on the aft wing and the propellers. The motor and propeller suitable for the design are chosen throug
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Srivathsan, Shreyas, Pranav Sridhar, Marilyn Smith, and Juergen Rauleder. "Experimental and Computational Investigations of Propeller-Wing Interactions." In Vertical Flight Society 80th Annual Forum & Technology Display. The Vertical Flight Society, 2024. http://dx.doi.org/10.4050/f-0080-2024-1337.

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A joint experimental-computational research campaign is underway to develop physical understanding and a validation-quality database for a model-scale tractor propeller-wing system. Separate load measurements on the wing and propeller accompany wing surface pressure distributions and flow field measurements via stereoscopic particle image velocimetry (SPIV) at discrete wing spanwise locations for a range of static propeller tilt angles. The physical wind tunnel test is modeled using a high-fidelity computational approach (Helios). Computational simulations aid in assessing the influence of the
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6

Kreshock, Andrew, Hao Kang, Hyeonsoo Yeo, and Robert Thornburgh. "Validation Of Comprehensive Modeling Of The Wing And Rotor Aeroelastic Test System." In Vertical Flight Society 72nd Annual Forum & Technology Display. The Vertical Flight Society, 2016. http://dx.doi.org/10.4050/f-0072-2016-11432.

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This paper uses a modular approach to validate the modeling process of the Wing and Rotor Aeroelastic Test System (WRATS) tiltrotor using two different rotorcraft comprehensive analyses: RCAS and CAMRAD II. The subcomponents used to build the models are first validated using experimental testing and ABAQUS three-dimensional and one-dimensional modeling. The assembled model is then used to predict the whirl-flutter stability boundary for two different configurations that were tested. Results show good agreement between the two analyses and previously measured wind-tunnel data for the first conf
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7

Uppoor, Vivek, Howard Zheng, and Inderjit Chopra. "High Advance Ratio Wind Tunnel Testing of a Slowed Mach-scaled Rotor with Full-Wing and Trailing Propeller Lift and Thrust Compounding." In Vertical Flight Society 81st Annual Forum and Technology Display. The Vertical Flight Society, 2025. https://doi.org/10.4050/f-0081-2025-343.

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Wind tunnel tests and comprehensive rotorcraft analysis were carried out on a slowed main rotor full-wing lift and thrust-compounded helicopter with a trailing propeller to investigate the effects of rotor and wing configuration on performance, blade structural loads, and hub vibratory loads. Experiments were conducted at advance ratios up to 0.7, incorporating three full-wing configurations with symmetric and asymmetric incidence angles and three different rotor shaft tilt angles. Propulsive thrust was measured by a trailing pusher propeller with its own balance system. The wind tunnel test d
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Kreshock, Andrew, Hyeonsoo Yeo, and Robert Thornburgh. "Comparison of Comprehensive Analyses Predicting Aeroelastic Stability of the Wing and Rotor Aeroelastic Test System." In Vertical Flight Society 74th Annual Forum & Technology Display. The Vertical Flight Society, 2018. http://dx.doi.org/10.4050/f-0074-2018-12761.

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Whirl flutter stability is a critical limitation for tiltrotor aircraft. This paper investigates whirl flutter predictions for the Wing and Rotor Aeroelastic Test System (WRATS) using comprehensive analysis, focusing on the comparison of the whirl flutter stability predictions between CARMAD II and RCAS. The analytical models have been created using a modular approach to systematically validate the modeling process of the WRATS tiltrotor. Comparison of non-rotating frequencies for blade, flexbeam, flexbeam and cuff, and blade with flexbeam and cuff shows excellent agreement between CAMRAD II a
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López Herreros, I., F. Arevalo Lozano, J. Barrera Rodríguez, A. Egido Fernández, M. Chimeno, and P. García-Fogeda Núñez. "A1.1 - The use of LIDAR to measure the flexion and torsion of a wing." In ETTC 2024 - European Test and Telemetry Conference. AMA Service GmbH, Von-Münchhausen-Str. 49, 31515 Wunstorf, 2024. https://doi.org/10.5162/ettc2024/a1.1.

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Phillips, Brandyn, Vikram Hrishikeshavan, and Inderjit Chopra. "Enhancing the Performance of a Quadrotor Biplane Tail-sitter (QBiT)." In Vertical Flight Society 74th Annual Forum & Technology Display. The Vertical Flight Society, 2018. http://dx.doi.org/10.4050/f-0074-2018-12688.

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To meet the performance demands of modern UAV operations, hybrid air vehicles that incorporate the speed and efficiency of fixed wing vehicles and the VTOL capabilities of rotorcraft have come to the forefront. This paper presents work being done to expand the performance of one such hybrid air vehicle, the quadrotor biplane. This vehicle takes flight in tail-sitter configuration and uses differential thrust vectors to pitch forward into forward flight configuration. This control method does not require conventional control surfaces, therefor making the system mechanically simple. The vehicle
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Berichte der Organisationen zum Thema "Wing test"

1

Mertaugh, Lawrence J. Naval Rotary Wing Aircraft Flight Test Squadron Flight Test Approval Process. Defense Technical Information Center, 1998. http://dx.doi.org/10.21236/ada350674.

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2

CALS TEST NETWORK WRIGHT-PATTERSON AFB OH. Technical Raster Transfer Using: 4950th/Test Wing/AMIS' DATA MIL-R-28002A (Raster) Quick Short Test Report. Defense Technical Information Center, 1993. http://dx.doi.org/10.21236/ada312302.

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3

Almanza, Joe, Lynn Thompson, and Mary Kruck. ADST System Test Report for the Rotary Wing Aircraft Airnet Aeromodel and Weapon Model Merge with the ATAC 2 Baseline. Defense Technical Information Center, 1994. http://dx.doi.org/10.21236/ada281580.

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4

KIRK WINTERHOLLER. HWMA/RCRA CLOSURE PLAN FOR THE MATERIALS TEST REACTOR WING (TRA-604) LABORATORY COMPONENTS VOLUNTARY CONSENT ORDER ACTION PLAN VCO-5.8 D REVISION2. Office of Scientific and Technical Information (OSTI), 2008. http://dx.doi.org/10.2172/924724.

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5

Biancalana, Cecilia. Italy’s multiple populisms facing the Russo-Ukrainian war. European Center for Populism Studies (ECPS), 2023. http://dx.doi.org/10.55271/rp0022.

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Italy has been defined as a laboratory for populism and a “populist paradise.” Indeed, multiple forms of populism coexist in Italy, covering the entire political spectrum. From the “left-wing” Movimento 5 Stelle to the right-wing coalition composed of Fratelli d’Italia, Forza Italia and the Lega, we can be sure that populism is very popular in Italy. We can be equally sure that, over the last few years, all these parties have had links to the Putin regime. Suffice it to mention the decades-long friendship between Silvio Berlusconi and Vladimir Putin or the admiration Matteo Salvini, the head o
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Ghee, Terence A., and Nigel J. Taylor. Low-Speed Wind Tunnel Tests on a Diamond Wing High Lift Configuration. Defense Technical Information Center, 2000. http://dx.doi.org/10.21236/ada377908.

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7

Verbeek, Bertjan, and Andrej Zaslove. Waking the Sleeping Populist Giant: The 2024 European Elections and Populism in the Netherlands. European Center for Populism Studies (ECPS), 2024. http://dx.doi.org/10.55271/rp0086.

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The results of the 2024 European elections for populist parties in the Netherlands are intimately related to the events in national Dutch politics since 2021. The relative success of the Party for Freedom (VVD) since 2023 has been related to its more moderate position on European integration and Islam. This change of tone was part of increasing the party’s credibility at home and abroad. The European elections were presented as a litmus test for the proposed centre-right government in the Netherlands, and they testified to the increased room for the populist vote in general and the increased c
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Ivaldi, Gilles. A Tipping Point for Far-Right Populism in France. European Center for Populism Studies (ECPS), 2024. http://dx.doi.org/10.55271/rp0070.

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The 2024 French European election took place against the backdrop of an economic and cost-of-living crisis in a context marked by global uncertainty arising from the war in Ukraine, social unrest and deep political discontent with President Emmanuel Macron. Marine Le Pen’s Rassemblement National (RN) emerged as the big winner with 31.4% of the vote, while Macron’s Renaissance list trailed far behind at 14.6%. Meanwhile, Jean-Luc Mélenchon’s left-wing populist La France Insoumise (LFI) won 9.9%, reflecting current internal dissent within the party and deep ideological divisions exposed by the I
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Tao, Yang, Amos Mizrach, Victor Alchanatis, Nachshon Shamir, and Tom Porter. Automated imaging broiler chicksexing for gender-specific and efficient production. United States Department of Agriculture, 2014. http://dx.doi.org/10.32747/2014.7594391.bard.

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Extending the previous two years of research results (Mizarch, et al, 2012, Tao, 2011, 2012), the third year’s efforts in both Maryland and Israel were directed towards the engineering of the system. The activities included the robust chick handling and its conveyor system development, optical system improvement, online dynamic motion imaging of chicks, multi-image sequence optimal feather extraction and detection, and pattern recognition. Mechanical System Engineering The third model of the mechanical chick handling system with high-speed imaging system was built as shown in Fig. 1. This syst
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Huskey, A., and T. Forsyth. NREL Small Wind Turbine Test Project: Mariah Power's Windspire Wind Turbine Test Chronology. Office of Scientific and Technical Information (OSTI), 2009. http://dx.doi.org/10.2172/957342.

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