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 9. Februar 2022

Geben Sie eine Quelle nach APA, MLA, Chicago, Harvard und anderen Zitierweisen an

Wählen Sie eine Art der Quelle aus:

Machen Sie sich mit den Listen der aktuellen Artikel, Bücher, Dissertationen, Berichten und anderer wissenschaftlichen Quellen zum Thema "Wing test" bekannt.

Neben jedem Werk im Literaturverzeichnis ist die Option "Zur Bibliographie hinzufügen" verfügbar. Nutzen Sie sie, wird Ihre bibliographische Angabe des gewählten Werkes nach der nötigen Zitierweise (APA, MLA, Harvard, Chicago, Vancouver usw.) automatisch gestaltet.

Sie können auch den vollen Text der wissenschaftlichen Publikation im PDF-Format herunterladen und eine Online-Annotation der Arbeit lesen, wenn die relevanten Parameter in den Metadaten verfügbar sind.

Zeitschriftenartikel zum Thema "Wing test"

1

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

Der volle Inhalt der Quelle
Annotation:
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 to control wing camber, which created additional lift. Wind tunnel tests were conducted to investigate the changes in lift and drag during wing folding and expansion, and to observe the influence of LIPCA actuation on the wing. In the tests, effects of the wing fold/expansion and actuation of LIPCA on changes in lift and drag were quantitatively identified.
APA, Harvard, Vancouver, ISO und andere Zitierweisen
2

Siliang, Du, und Tang Zhengfei. „The Aerodynamic Behavioral Study of Tandem Fan Wing Configuration“. International Journal of Aerospace Engineering 2018 (30.10.2018): 1–14. http://dx.doi.org/10.1155/2018/1594570.

Der volle Inhalt der Quelle
Annotation:
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 aerodynamic characteristic interaction rule between the front and rear fan wings was analyzed. In addition, the wind test model of a tandem fan wing was designed, and the results of the wind tunnel test and numerical calculation results were compared to verify the preliminary setup. The results show that at a certain height, distance, and installation angle, aerodynamic characteristics of a tandem fan wing have more advantages compared to the single fan wing. Therefore, the tandem fan wing aircraft’s advantages have good prospects for development and application.
APA, Harvard, Vancouver, ISO und andere Zitierweisen
3

Teo, Z. W., T. H. New, Shiya Li, T. Pfeiffer, B. Nagel und V. Gollnick. „Wind tunnel testing of additive manufactured aircraft components“. Rapid Prototyping Journal 24, Nr. 5 (09.07.2018): 886–93. http://dx.doi.org/10.1108/rpj-06-2016-0103.

Der volle Inhalt der Quelle
Annotation:
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. Findings Additive manufacturing provides cost-effective wing components for wind tunnel test components with fast turn-around time. They can be used with confidence if the wing deflections could be accounted for systematically and accurately, especially at the region of aerodynamic stall. Research limitations/implications Significant wing flutter and unsteady deflections were encountered at higher test velocities and pitch angles. This reduced the accuracy in which the wing deflections could be corrected. Additionally, wing twists could not be quantified as effectively because of camera perspectives. Originality/value This paper shows that additive manufacturing can be used to fabricate aircraft test components with satisfactory strength and quantifiable deflections for wind tunnel testing, especially when the designs are significantly complex and thin.
APA, Harvard, Vancouver, ISO und andere Zitierweisen
4

Tsushima, Natsuki, Kenichi Saitoh, Hitoshi Arizono und Kazuyuki Nakakita. „Structural and Aeroelastic Studies of Wing Model with Metal Additive Manufacturing for Transonic Wind Tunnel Test by NACA 0008 Example“. Aerospace 8, Nr. 8 (25.07.2021): 200. http://dx.doi.org/10.3390/aerospace8080200.

Der volle Inhalt der Quelle
Annotation:
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 environment. The additive manufacturing technique may help to reduce the expensive testing cost and allows investigation of aeroelastic characteristics of new designs in aerospace structures as needed. In this paper, a metal wing model made with the additive manufacturing technique for a transonic flutter test is studied. Structural/aeroelastic characteristics of an additively manufactured wing model are evaluated numerically and experimentally. The transonic wind tunnel experiment demonstrated the feasibility of the metal AM-based wings in a transonic flutter wind tunnel testing showing the capability to provide reliable experimental data, which was consistent with numerical solutions.
APA, Harvard, Vancouver, ISO und andere Zitierweisen
5

Rogalla, Svana, Liliana D'Alba, Ann Verdoodt und Matthew D. Shawkey. „Hot wings: thermal impacts of wing coloration on surface temperature during bird flight“. Journal of The Royal Society Interface 16, Nr. 156 (Juli 2019): 20190032. http://dx.doi.org/10.1098/rsif.2019.0032.

Der volle Inhalt der Quelle
Annotation:
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 tunnel and measured wing surface temperature at realistic flight speeds. Even under simulated flight conditions, darker wings consistently became hotter than pale wings. In white wings with black tips, the temperature differential produced convective currents towards the darker wing tips that could lead to an increase in lift. Additionally, a temperature differential between wing-spanning warm muscles and colder flight feathers could delay the flow separation above the wing, increasing flight efficiency. Together, these results suggest that wing coloration and muscle temperature both play important roles in modulating wing surface temperature and therefore potentially flight efficiency.
APA, Harvard, Vancouver, ISO und andere Zitierweisen
6

Zafirov, Dimo, und Hristian Panayotov. „Joined-wing test bed UAV“. CEAS Aeronautical Journal 6, Nr. 1 (07.10.2014): 137–47. http://dx.doi.org/10.1007/s13272-014-0134-z.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
7

Kumar, G. C. Vishnu, und M. Rahamath Juliyana. „Design and Analysis of Flapping Wing“. Applied Mechanics and Materials 110-116 (Oktober 2011): 3495–99. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.3495.

Der volle Inhalt der Quelle
Annotation:
This paper the optimum wing planform for flapping motion is investigated by measuring the lift and drag characteristics. A model is designed with a fixed wing and two flapping wings attached to its trailing edge. Using wind tunnel tests are conducted to study the effect of angle of attack (smoke flow visualization technique). The test comprises of measuring the aerodynamic forces with flapping motion and without it for various flapping frequencies and results are presented. It can be possible to produce a micro air vehicle which is capable of stealthy operations for defence requirements by using these experimental data.
APA, Harvard, Vancouver, ISO und andere Zitierweisen
8

Khaghaninia, S., S. Mohammadi, A. Srafrazi, K. Nejad und R. Zahiri. „Geometric Morphometric Study on Geographic Dimorphism of Coding Moth Cydia Pomonella (Lepidoptera, Tortricidae) from North West of Iran“. Vestnik Zoologii 45, Nr. 5 (01.01.2011): e-20-e-28. http://dx.doi.org/10.2478/v10058-011-0028-z.

Der volle Inhalt der Quelle
Annotation:
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 correlation analysis (CCA) revealed significant correlation between environmental parameters and wing shape variables. Among environmental parameters, wind speed showed the highest correlation with wing shape variables whereas, the correlation between latitude, relative humidity as well as amount of precipitation and wing shape variables was low. Considering the effect of various environmental parameters on wing shape, wind speed was determined as important parameter affecting geographic dimorphism. Among the populations collected from different regions, two geographic population pairs; Meshkinshahr-Mahneshan and Zandjan-Khoramdareh were selected as representative of low and high windy regions, respectively. Relative warp analysis (RWA) of fore and hind wings shape variables in the areas with high and low wind showed shorter and wider fore wings as well as slender and narrower hind wings in populations from high windy regions compared with populations from low wind regions. Centroid size of fore and hind wings in high windy area populations were smaller compared with those from low windy ones as revealed by t-test. The results showed aerodynamic shape and small size of wings are as adapted traits for powerful flight and its control in high windy regions.
APA, Harvard, Vancouver, ISO und andere Zitierweisen
9

Streit, T., und C. Hoffrogge. „DLR transonic inverse design code, extensions and modifications to increase versatility and robustness“. Aeronautical Journal 121, Nr. 1245 (11.10.2017): 1733–57. http://dx.doi.org/10.1017/aer.2017.101.

Der volle Inhalt der Quelle
Annotation:
ABSTRACTThe DLR inverse design code computes the wing geometry for a prescribed target pressure distribution. It is based on the numerical solution of the integral inverse transonic small perturbation (TSP) equations. In this work, several extensions and modifications of the inverse design code are described. Results are validated with corresponding redesign test cases. The first modification concerns applications for high transonic Mach numbers or cases with strong shocks. The introduced modifications enable converged design solutions for cases where the original method failed. The second modification is the extension of the code to general non-planar wings. Previously, the design code was restricted to non-planar wing designs with small dihedral or to nacelle design. A third modification concerns aerofoil/wings designed for wind-tunnel design. In order to design a swept wing between two wind-tunnel walls, the solution method was extended to two symmetry planes. The introduced extensions and modifications have increased the robustness and range of applicability of the inverse design code.
APA, Harvard, Vancouver, ISO und andere Zitierweisen
10

Zhang, Ming Lu, Yi Ren Yang und Zhi Yong Lu. „Unsteady Characteristics over Dynamic Delta Wings“. Applied Mechanics and Materials 128-129 (Oktober 2011): 350–53. http://dx.doi.org/10.4028/www.scientific.net/amm.128-129.350.

Der volle Inhalt der Quelle
Annotation:
A study of flow and frequency characteristics of the leading-edge vortices over a delta wing undergoing pitching up-stop motions is presented. The experiments with the dynamic delta wings were conducted in a water channel and a wind tunnel respectively. Among them, the test of the flow visualization was completed in the water channel with the delta wing with pitching up-stop motions. The result shows that in the case of pitching up-stop movement the vortex breakdown position is dependent on the range of incidence at which the wing is subject to pitching up-stop and the reduced frequency k (k=c/2U∞). Analysis of the pressure signal measured in the wind tunnel shows when the delta wing is subject to pitching-up the nondimensional spiral wave frequency at nominal incidence in post-breakdown is higher than that at corresponding static state and the bigger the k is, the higher the nondimensional spiral wave frequency is. The same conclusion is fitted with different sweep delta wing.
APA, Harvard, Vancouver, ISO und andere Zitierweisen
Mehr Quellen

Dissertationen zum Thema "Wing test"

1

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.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
2

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.

Der volle Inhalt der Quelle
Annotation:
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 wing's tip, which is the idea extracted from Dowell's work, so that the torsion and bending modes are coupled (torsional moment of inertia reduction). The aeroelastic model can be divided into two parts: First, the wings structural dynamic models are computed using the finite element method implements in NASTRAN solver. sequently, ZAERO software is employed to compute the aeroelastic model. Unsteady aerodynamic loading is computed through a lifting surface interference method known as ZONA 6. The wing models defined as test beds will be constructed and tested in different wind tunnels, including open and closed tests section types. The power spectral density approach might be employed as a way to identify flutter. The output signal from an accelerometer placed in the wing structure allows, through its power spectral density computation, the identification of flutter onset condition and the corresponding undisturbed flow speed. The PSD function increase means flow energy extraction, a condition to have flutter. Experimental flutter speeds are close to the theoretically computed ones by ZAERO. From these observations, it is possible to validate the aeroelastic theoretical model in a small disturbance context. After flutter onset , the limit cycle oscillations are observed, fed by freestream energy extraction. The aeroelastic models under investigation in this research are excellent models for nonlinear aeroelastic phenomena behavior study.
APA, Harvard, Vancouver, ISO und andere Zitierweisen
3

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.

Der volle Inhalt der Quelle
Annotation:
Thesis (MScEng (Electrical and Electronic Engineering))--University of Stellenbosch, 2006.
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 to allow sensors and actuators to be arbitrarily added to the system, based on the CAN standard. A CAN sensor node was developed that could digitize 12 channels at up to 16 bit resolution and do basic filtering of the data. Onboard computing was provided by a PC/104 based computer running Linux, with additional hardware added to interface with the CAN bus and assist with timing. A simulation environment for the helicopter was evaluated and shown to provide a good test bed for the control of the helicopter. Finally, the avionics was used during piloted test-flights to measure data and judge the performance of both the modified helicopter and the electronics itself.
APA, Harvard, Vancouver, ISO und andere Zitierweisen
4

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.

Der volle Inhalt der Quelle
Annotation:
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 remotely piloted vehicle (RPV) serves as the initial design point. The aeroelastic response of the final design is verified against the response of the full-scale model. Reasonable agreement is seen in both aeroelastic damping and frequency for a range of flight velocities, but some discrepancy remains in accurately capturing the flutter velocity.
Master of Science
APA, Harvard, Vancouver, ISO und andere Zitierweisen
5

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.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
6

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.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
7

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.

Der volle Inhalt der Quelle
Annotation:
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 accurately measure and capture the configuration\'s potential for structural nonlinearity, the test article must exhibit equivalent structural flexibility and be designed to meet airworthiness standards. Previous work has demonstrated airworthiness through the successful flight of a Geometrically Scaled Remotely Piloted Vehicle. The work presented in this thesis involves evaluation of an aeroelastically tuned design through ground-based experimentation. The result of these experimental investigations has led to the conclusion that a full redesign of the forward and aft wings must be completed to demonstrate sufficient geometric nonlinearity for the follow-on Aeorelastically Tuned Remotely Piloted Vehicle. This thesis also presents flight test plans for the aeroelastically tuned RPV.
Master of Science
APA, Harvard, Vancouver, ISO und andere Zitierweisen
8

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.

Der volle Inhalt der Quelle
Annotation:
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 use of the effective width method allied to a large scale, linear finite element analysis. The work includes the development of a new method o-F construction for composite box structures. The wing skin sti-Ffeners and rib flanges are co-cured together. Integral slotted Joint features are formed in each part. The structure is then adhesively bonded together. A full description of the manufacture o-F the wing box is included. The structure was also tested in a specially designed rig. It was tested to ultimate design loads in: i) Positive bending to 13.33. ii) Negative bending to -96. iii) Pure torsion resulting from full aileron load. iv) Torsion with 96 bending. The compression panels were seen to postbuckle and recover in each load case. Results are compared with theory, and with the original aluminium Al wing. The structure is 257. lighter than its aluminium counterpart. Finally, suggestions are made for possible areas of further research.
APA, Harvard, Vancouver, ISO und andere Zitierweisen
9

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/.

Der volle Inhalt der Quelle
Annotation:
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. During the phases of the project, particular attention was given to the geometry and the materials used, in order to trigger the flutter for low flow velocity. The CAD software SolidWorks® was used for the design of the wing and then the drawings were sent to the Clarkson machine shop in order to to produce the parts required by the wing assembly. FEM simulations were performed, using software MSC NASTRAN/PATRAN®, to evaluate the stiffness of the whole wing as well as the natural vibration modes of the structure. These data, in a first approximation, were used to predict the flutter speed. Finally, experimental tests in the Clarkson wind tunnel facility were carried out in order to validate the results obtained from FEM analysis. The power collected by the piezoelectrics under flutter condition was addressed by tuning the resistors downstream the electronic circuit of the piezoelectrics.
APA, Harvard, Vancouver, ISO und andere Zitierweisen
10

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.

Der volle Inhalt der Quelle
Annotation:
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 custom instrumentation package is also presented along with the setup, procedure and results from all testing. Results are presented for a wind tunnel test for air data boom calibration, propulsion system static thrust testing, a bifilar pendulum test for experimental calculation of mass moments of inertia, a static structural loading test for structural design validation, a full taxi test and a successful first flight.
Master of Science
APA, Harvard, Vancouver, ISO und andere Zitierweisen
Mehr Quellen

Bücher zum Thema "Wing test"

1

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

Den vollen Inhalt der Quelle finden
APA, Harvard, Vancouver, ISO und andere Zitierweisen
2

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

Den vollen Inhalt der Quelle finden
APA, Harvard, Vancouver, ISO und andere Zitierweisen
3

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

Den vollen Inhalt der Quelle finden
APA, Harvard, Vancouver, ISO und andere Zitierweisen
4

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

Den vollen Inhalt der Quelle finden
APA, Harvard, Vancouver, ISO und andere Zitierweisen
5

Lance, Michael B. Low-speed wind-tunnel test of an unpowered high-speed stoppable rotor concept in fixed-wing mode. [Washington, D.C.]: National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division, 1991.

Den vollen Inhalt der Quelle finden
APA, Harvard, Vancouver, ISO und andere Zitierweisen
6

Lance, Michael B. Low-speed wind-tunnel test of an unpowered high-speed stoppable rotor concept in fixed-wing mode. Hampton, Va: Langley Research Center, 1991.

Den vollen Inhalt der Quelle finden
APA, Harvard, Vancouver, ISO und andere Zitierweisen
7

Yip, Long P. Static wind-tunnel and radio-controlled flight test investigation of a remotely piloted vehicle having a delta wing planform. Hampton, Va: Langley Research Center, 1990.

Den vollen Inhalt der Quelle finden
APA, Harvard, Vancouver, ISO und andere Zitierweisen
8

Yip, Long P. Static wind-tunnel and radio-controlled flight test investigation of a remotely piloted vehicle having a delta wing planform. Hampton, Va: Langley Research Center, 1990.

Den vollen Inhalt der Quelle finden
APA, Harvard, Vancouver, ISO und andere Zitierweisen
9

Larson, Richard R. Flight control system development and flight test experience with the F-111 mission adaptive wing aircraft. Edwards, Calif: National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, 1986.

Den vollen Inhalt der Quelle finden
APA, Harvard, Vancouver, ISO und andere Zitierweisen
10

MacKinnon, A. Wind tunnel tests on a variable camber wing. Cranfield, Bedford, England: College of Aeronautics, Cranfield University, 1993.

Den vollen Inhalt der Quelle finden
APA, Harvard, Vancouver, ISO und andere Zitierweisen
Mehr Quellen

Buchteile zum Thema "Wing test"

1

Liu, Jihai, Yingsong Gu, Ke Xie und Pengtao Shi. „Flutter Modeling, Analysis and Test for Blended-Wing-Body Flying Wing“. In Lecture Notes in Electrical Engineering, 979–84. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_78.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
2

Fu, Zhichao, und Ziqiang Liu. „Nonlinear Flutter Test of a Very Flexible Wing“. In Lecture Notes in Electrical Engineering, 2627–40. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_211.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
3

Heryawan, Yudi, Hoon Cheol Park, Nam Seo Goo, Kwang Joon Yoon und Yung Hwan Byun. „Structural Design, Manufacturing, and Wind Tunnel Test of a Small Expandable Wing“. In Fracture and Strength of Solids VI, 1157–62. Stafa: Trans Tech Publications Ltd., 2006. http://dx.doi.org/10.4028/0-87849-989-x.1157.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
4

Streit, Thomas, Heiko Geyr von Schweppenburg, David Cruz und 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.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
5

Zárate, José, und Hartmut Witte. „Design and Control of a Flapping Wing System Test Bench“. In Advances in Service and Industrial Robotics, 34–42. Cham: Springer International Publishing, 2019. http://dx.doi.org/10.1007/978-3-030-19648-6_5.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
6

Niu, Peixing, Yu Zheng, Xu Zeng und Xiaoguang Li. „Design and Flight Test Validation of a Rotor/Fixed-Wing UAV“. In Lecture Notes in Electrical Engineering, 1566–75. Singapore: Springer Singapore, 2019. http://dx.doi.org/10.1007/978-981-13-3305-7_125.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
7

Renson, L., J. P. Noël, D. A. W. Barton, S. A. Neild und G. Kerschen. „Nonlinear Phase Separation Testing of an Experimental Wing-Engine Structure“. In Rotating Machinery, Hybrid Test Methods, Vibro-Acoustics & Laser Vibrometry, Volume 8, 115–17. Cham: Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-54648-3_12.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
8

Spivey, Natalie, Rachel Saltzman, Carol Wieseman, Kevin Napolitano und Benjamin Smith. „Passive Aeroelastic Tailored Wing Modal Test Using the Fixed Base Correction Method“. In Topics in Modal Analysis & Testing, Volume 8, 61–83. Cham: Springer International Publishing, 2020. http://dx.doi.org/10.1007/978-3-030-47717-2_7.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
9

Kim, Nak-Hwe, und Jun-Ho Huh. „Designing 3D Propeller by Applying Bird’s Wing and Making a Test Product“. In Lecture Notes in Electrical Engineering, 811–17. Singapore: Springer Singapore, 2018. http://dx.doi.org/10.1007/978-981-13-1328-8_106.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
10

Ruiterkamp, Richard, und Sören Sieberling. „Description and Preliminary Test Results of a Six Degrees of Freedom Rigid Wing Pumping System“. In Airborne Wind Energy, 443–58. Berlin, Heidelberg: Springer Berlin Heidelberg, 2013. http://dx.doi.org/10.1007/978-3-642-39965-7_26.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen

Konferenzberichte zum Thema "Wing test"

1

Scherer, Lewis B., Christopher A. Martin, Kari Appa, Jayanth N. Kudva und Mark N. West. „Smart wing wind tunnel test results“. In Smart Structures and Materials '97, herausgegeben von Janet M. Sater. SPIE, 1997. http://dx.doi.org/10.1117/12.274694.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
2

Reichenbach, Eric, Mark Castelluccio und Bradley Sexton. „Joined Wing Sensorcraft Aeroservoelastic Wind Tunnel Test Program“. In 52nd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2011. http://dx.doi.org/10.2514/6.2011-1956.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
3

Britt, Robert, Daniel Ortega, John Mc Tigue und Matthew Scott. „Wind Tunnel Test of a Very Flexible Aircraft Wing“. In 53rd AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics and Materials Conference
20th AIAA/ASME/AHS Adaptive Structures Conference
14th AIAA. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2012. http://dx.doi.org/10.2514/6.2012-1464.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
4

Begnini, Guilherme R., Carlos A. Bones und Cleber Spode. „Transonic Wind Tunnel Test of Wing Oscillating in Pitch“. In 2018 Applied Aerodynamics Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2018. http://dx.doi.org/10.2514/6.2018-3004.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
5

Goizueta, Norberto, Ariel Drachinsky, Andrew Wynn, Daniella E. Raveh und Rafael Palacios. „Flutter predictions for very flexible wing wind tunnel test“. In AIAA Scitech 2021 Forum. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2021. http://dx.doi.org/10.2514/6.2021-1711.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
6

HICKS, JOHN, und BRYAN MOULTON. „Effects of maneuver dynamics on drag polars of the X-29A forward-swept-wing aircraft with automatic wing camber control“. In 4th Flight Test Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-2144.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
7

Yokozeki, Tomohiro, Aya Sugiura und Yoshiyasu Hirano. „Development and Wind Tunnel Test of Variable Camber Morphing Wing“. In 22nd AIAA/ASME/AHS Adaptive Structures Conference. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-1261.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
8

Scherer, Lewis B., C. A. Martin, Brian P. Sanders, Mark N. West, Jennifer L. Pinkerton-Florance, Carol D. Wieseman, Alpheus W. Burner und Gary A. Fleming. „DARPA/AFRL Smart Wing Phase 2 wind tunnel test results“. In SPIE's 9th Annual International Symposium on Smart Structures and Materials, herausgegeben von Anna-Maria R. McGowan. SPIE, 2002. http://dx.doi.org/10.1117/12.475104.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
9

Scherer, Lewis B., Christopher A. Martin, Mark N. West, Jennifer P. Florance, Carol D. Wieseman, Alpheus W. Burner und Gary A. Fleming. „DARPA/ARFL/NASA Smart Wing second wind tunnel test results“. In 1999 Symposium on Smart Structures and Materials, herausgegeben von Jack H. Jacobs. SPIE, 1999. http://dx.doi.org/10.1117/12.351563.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
10

BONNEMA, KENNETH, und STEPHEN SMITH. „AFTI/F-111 Mission Adaptive Wing flight research program“. In 4th Flight Test Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1988. http://dx.doi.org/10.2514/6.1988-2118.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen

Berichte der Organisationen zum Thema "Wing test"

1

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

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
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. Fort Belvoir, VA: Defense Technical Information Center, August 1993. http://dx.doi.org/10.21236/ada312302.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
3

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

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
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), Februar 2008. http://dx.doi.org/10.2172/924724.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
5

Ghee, Terence A., und Nigel J. Taylor. Low-Speed Wind Tunnel Tests on a Diamond Wing High Lift Configuration. Fort Belvoir, VA: Defense Technical Information Center, Juni 2000. http://dx.doi.org/10.21236/ada377908.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
6

Huskey, A., und T. Forsyth. NREL Small Wind Turbine Test Project: Mariah Power's Windspire Wind Turbine Test Chronology. Office of Scientific and Technical Information (OSTI), Juni 2009. http://dx.doi.org/10.2172/957342.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
7

Schroeder, John. The Great Plains Wind Power Test Facility. Office of Scientific and Technical Information (OSTI), Januar 2014. http://dx.doi.org/10.2172/1117320.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
8

Tuten, James Maner, Imtiaz Haque und Nikolaos Rigas. Clemson University Wind Turbine Drivetrain Test Facility. Office of Scientific and Technical Information (OSTI), März 2016. http://dx.doi.org/10.2172/1324502.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
9

Bollmeier, W. S. II, und D. M. Dodge. Cooperative field test program for wind systems. Office of Scientific and Technical Information (OSTI), März 1992. http://dx.doi.org/10.2172/5285410.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
10

Karlson, Benjamin, Bryan Miller und Jason Biddle. Wind Turbine/Radar Interference: Offshore Test Options. Office of Scientific and Technical Information (OSTI), September 2014. http://dx.doi.org/10.2172/1762101.

Der volle Inhalt der Quelle
APA, Harvard, Vancouver, ISO und andere Zitierweisen
Die Auswahlen zum Thema "Wing test" für konkrete Quellenarten können Sie auch interessieren:
Zeitschriftenartikel Dissertationen Bücher
Wir bieten Rabatte auf alle Premium-Pläne für Autoren, deren Werke in thematische Literatursammlungen aufgenommen wurden. Kontaktieren Sie uns, um einen einzigartigen Promo-Code zu erhalten!

Zur Bibliographie