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Journal articles on the topic 'Wing test'

Author: Grafiati

Published: 28 June 2021

Last updated: 9 February 2022

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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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2

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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3

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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4

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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6

Zafirov, Dimo, and Hristian Panayotov. "Joined-wing test bed UAV." CEAS Aeronautical Journal 6, no. 1 (2014): 137–47. http://dx.doi.org/10.1007/s13272-014-0134-z.

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

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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 usi

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8

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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9

Streit, T., and C. Hoffrogge. "DLR transonic inverse design code, extensions and modifications to increase versatility and robustness." Aeronautical Journal 121, no. 1245 (2017): 1733–57. http://dx.doi.org/10.1017/aer.2017.101.

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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 mod

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10

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

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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

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11

Combes, S. A., and T. L. Daniel. "Shape, flapping and flexion: wing and fin design for forward flight." Journal of Experimental Biology 204, no. 12 (2001): 2073–85. http://dx.doi.org/10.1242/jeb.204.12.2073.

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SUMMARY Both kinematics and morphology are critical determinants of performance in flapping flight. However, the functional consequences of changes in these traits are not yet well understood. Traditional aerodynamic studies of planform wing shape have suggested that high-aspect-ratio wings generate more force per area and perform more efficiently than low-aspect-ratio wings, but these analyses may neglect critical components of flapping flight such as unsteady fluid dynamics and wing or fin flexion. In this paper, we use an unsteady potential flow analysis that incorporates wing flexion to te

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Bauknecht, Andŕe, Xing Wang, Jan-Arun Faust, and Inderjit Chopra. "Wind Tunnel Test of a Rotorcraft with Lift Compounding." Journal of the American Helicopter Society 66, no. 1 (2021): 1–16. http://dx.doi.org/10.4050/jahs.66.012002.

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Rotorcraft flight speed is limited by compressibility effects on the advancing blade side and decreasing lift potential on the retreating blade side. It may thus be beneficial to employ a hingeless rotor to generate additional lift with the advancing blade and compensate the resulting rolling moment with a fixed wing on the retreating blade side. This concept is a form of "lift compounding" that appears to show enormous potential. The present paper presents results of a wind tunnel test with a slowed, hingeless rotor and single fixed wing on the retreating blade side. Based on rotor test stand

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13

Bond, Vanessa L., Robert A. Canfield, Maria da Luz Madruga Santos Matos, Afzal Suleman, and Maxwell Blair. "Joined-Wing Wind-Tunnel Test for Longitudinal Control via Aftwing Twist." Journal of Aircraft 47, no. 5 (2010): 1481–89. http://dx.doi.org/10.2514/1.41140.

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14

Yu, Li, Bin Bin Lv, Hong Tao Guo, Yu Yan, Xing Hua Yang, and Jian Guo Luo. "Research on Transonic Wind Tunnel Flutter Test for a Wing Model." Advanced Materials Research 1006-1007 (August 2014): 26–29. http://dx.doi.org/10.4028/www.scientific.net/amr.1006-1007.26.

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This paper adopts self-designed wing model to conduct flutter test on subsonic and transonic, and obtains flutter characteristic of the model, and the test results are used for calibration and verification of flutter procedures. The sub-critical extrapolation is used to obtain the flutter sub-critical parameters and the direct observation method is used to obtain comparison of results. Error of results obtained by the two approaches does not exceed 5%, and validates reliability of the sub-critical prediction approach in continuous adjusted dynamic pressure flutter test.

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15

Ölçmen, Semih M., and Roger L. Simpson. "Influence of Passive Flow-Control Devices on the Pressure Fluctuations at Wing-Body Junction Flows." Journal of Fluids Engineering 129, no. 8 (2007): 1030–37. http://dx.doi.org/10.1115/1.2746917.

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The effectiveness of passive flow-control devices in eliminating high surface rms pressure fluctuations at the junction of several idealized wing/body junction flows was studied. Wall-pressure fluctuation measurements were made using microphones along the line of symmetry at the wing/body junction of six different wing shapes. The wings were mounted on the wind tunnel floor at a zero degree angle-of-attack. The six wing shapes tested were: a 3:2 semi-elliptical-nosed NACA 0020 tailed generic body shape (Rood wing), a parallel center-body model, a tear-drop model, a Sandia 1850 model, and NACA

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Mat, Shabudin, I. Shah Ishak, Khidzir Zakaria, and Z. Ajis Khan. "Manufacturing Process of Blended Delta-Shaped Wing Model." Advanced Materials Research 845 (December 2013): 971–74. http://dx.doi.org/10.4028/www.scientific.net/amr.845.971.

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Aerodynamicists have long acknowledged the blended wing body (BWB) aircraft design could produce great aerodynamic advantages due to the integration of the delta wing structure with the thick center body. Therefore the wind tunnel test campaign is crucial to gain information of the flow field that governs the delta-shaped wing which has frequently baffled the aerodynamicists. In such, the wind tunnel test required acceptable quality of delta-shaped wing model for results validity. Consequently, the manufacturing process as well as the selection of the appropriate machinery tools, must be wisel

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17

Tjahjowidodo, Tegoeh, and Shian Lee. "Tendon-Sheath Mechanisms in Flexible Membrane Wing Mini-UAVs: Control and Performance." International Journal of Aerospace Engineering 2017 (2017): 1–18. http://dx.doi.org/10.1155/2017/8181743.

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Flexible membrane wings (FMWs) are known for two inherent advantages, that is, adaptability to gusty airflow as the wings can flex according to the gust load to reduce the effective angle of attack and the ability to be folded for compact storage purposes. However, the maneuverability of UAV with FMWs is rather limited as it is impossible to install conventional ailerons. The maneuver relies only on the rudders. Some applications utilize torque rods to warp the wings, but this approach makes the FMW become unfoldable. In this research, we proposed the application of a tendon-sheath mechanism t

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18

Jiang, Shan, Yong Hu, Qiang Li, et al. "The Noise-Reduction Characteristics of Microstructure of Dragonfly Wing Leading Vein." Applied Sciences 11, no. 7 (2021): 2970. http://dx.doi.org/10.3390/app11072970.

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Dragonfly wings have many excellent functions, such as superhydrophobic, fatigue resistance, anti-reflection, etc. However, there are few reports on the low noise flight of dragonfly wings. For this reason, the microgeometry of dragonfly wings was studied in this paper to reveal the mechanism of low-noise flight of dragonfly leading veins. The micromorphology of dragonfly wings was observed by scanning electron microscopy. It was found that the leading-edge veins of dragonfly wings have a triangular prism-like serrated structure, which has been proven to have the effect of improving aeroacoust

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19

Pelehach, Laura. "On a Wing and a Test Tube." Laboratory Medicine 28, no. 4 (1997): 283–84. http://dx.doi.org/10.1093/labmed/28.4.284.

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20

AOKI, Y., T. ISHIKAWA, S. TAKEDA, Y. HAYAKAWA, A. HARADA, and H. KIKUKAWA. "Fatigue test of lightweight composite wing structure." International Journal of Fatigue 28, no. 10 (2006): 1109–15. http://dx.doi.org/10.1016/j.ijfatigue.2006.02.017.

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21

Coton, F. N., R. A. McD. Galbraith, and R. B. Green. "The effect of wing planform shape on dynamic stall." Aeronautical Journal 105, no. 1045 (2001): 151–59. http://dx.doi.org/10.1017/s0001924000092071.

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AbstractThis paper examines the dynamic stalling of three wing planforms and characterises the main features of the stalling process in each case. The particular data were obtained during a three year research programme in the Department of Aerospace Engineering, University of Glasgow to collect high-resolution unsteady pressure data on the dynamic stalling characteristics of finite wing planforms. In this study, which was motivated by the pressing need for a greater understanding of the strongly three-dimensional effects in the tip region of helicopter rotors, the three wing planforms conside

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22

Lees, John J., Grigorios Dimitriadis, and Robert L. Nudds. "The influence of flight style on the aerodynamic properties of avian wings as fixed lifting surfaces." PeerJ 4 (October 20, 2016): e2495. http://dx.doi.org/10.7717/peerj.2495.

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The diversity of wing morphologies in birds reflects their variety of flight styles and the associated aerodynamic and inertial requirements. Although the aerodynamics underlying wing morphology can be informed by aeronautical research, important differences exist between planes and birds. In particular, birds operate at lower, transitional Reynolds numbers than do most aircraft. To date, few quantitative studies have investigated the aerodynamic performance of avian wings as fixed lifting surfaces and none have focused upon the differences between wings from different flight style groups. Dri

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23

Xu, Xin, Qiang Li, Dawei Liu, Keming Cheng, and Dehua Chen. "Geometric Effects Analysis and Verification of V-Shaped Support Interference on Blended Wing Body Aircraft." Applied Sciences 10, no. 5 (2020): 1596. http://dx.doi.org/10.3390/app10051596.

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A special V-shaped support for blended wing body aircraft was designed and applied in high-speed wind tunnel tests. In order to reduce the support interference and explore the design criteria of the V-shaped support, interference characteristics and geometric parameter effects of V-shaped support on blended wing body aircraft were numerically studied. According to the numerical results, the corresponding dummy V-shaped supports were designed and manufactured, and verification tests was conducted in a 2.4 m × 2.4 m transonic wind tunnel. The test results were in good agreement with the numerica

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24

Shi, Pengtao, Jihai Liu, Yingsong Gu, Zhichun Yang, and Pier Marzocca. "Full-Span Flying Wing Wind Tunnel Test: A Body Freedom Flutter Study." Fluids 5, no. 1 (2020): 34. http://dx.doi.org/10.3390/fluids5010034.

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Aiming at the experimental test of the body freedom flutter for modern high aspect ratio flexible flying wing, this paper conducts a body freedom flutter wind tunnel test on a full-span flying wing flutter model. The research content is summarized as follows: (1) The full-span finite element model and aeroelastic model of an unmanned aerial vehicle for body freedom flutter wind tunnel test are established, and the structural dynamics and flutter characteristics of this vehicle are obtained through theoretical analysis. (2) Based on the preliminary theoretical analysis results, the design and m

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25

Breen, John E., Michael E. Kreger, Christopher D. White, and Gordon C. Clark. "Field evaluation and model test of a composite wing-girder bridge." Canadian Journal of Civil Engineering 14, no. 6 (1987): 753–62. http://dx.doi.org/10.1139/l87-113.

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This paper presents the key observations and conclusions from the evaluation of an innovative "loose-fit" composite, post-tensioned concrete wing-girder bridge proposed for an elevated interstate highway expansion in an urban environment. The evaluation program included both testing to destruction of a 1/2-scale model of a partial span as well as construction monitoring and field testing at service load levels of a full-scale prototype two-span bridge. Results of both construction measurements and loading tests were compared with analytical predictions. Laboratory tests showed the composite be

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Kim, Kijoon, Seungkeun Kim, Jinyoung Suk, Jongmin Ahn, Nakwan Kim, and Byoung-Soo Kim. "Flight test of flying-wing type unmanned aerial vehicle with partial wing-loss." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 5 (2018): 1611–28. http://dx.doi.org/10.1177/0954410018758497.

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This paper investigates experimental evaluation via flight tests for applying adaptive neural network controller to a flying-wing type unmanned aerial vehicle experiencing partial wing-loss. For this, six-degree-of-freedom numerical model is constructed taking into account damage-induced changes to the unmanned aerial vehicle in aerodynamic coefficients, mass, center of gravity, and moments of inertia. Numerical simulations are performed to investigate the flight dynamics change and to verify the performance of the neural network based controller. During the flight test, main wing-loss is arti

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27

Cutts, C., and J. Speakman. "ENERGY SAVINGS IN FORMATION FLIGHT OF PINK-FOOTED GEESE." Journal of Experimental Biology 189, no. 1 (1994): 251–61. http://dx.doi.org/10.1242/jeb.189.1.251.

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Fifty-four skeins of pink-footed geese (Anser brachyrhynchus) were photographed from directly underneath to eliminate the effects of perspective distortion, and the wing-tip spacings (the distance between adjacent birds' wing tips perpendicular to the flight path at maximum wingspan) and depths (the distance between adjacent birds' body centres parallel to the flight path) were measured at the same time as local wind speeds. The photographs were used to test for savings in induced power from wing positioning relative to the predicted positions of vortices generated by other wings, using a theo

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28

I. Ismail, N., H. Yusoff, Hazim Sharudin, Arif Pahmi, H. Hafi, and Mahadzir M.M. "Lift distribution of washout twist morphing MAV wing." International Journal of Engineering & Technology 7, no. 4.13 (2018): 89. http://dx.doi.org/10.14419/ijet.v7i4.13.21337.

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Micro Air Vehicle, or also commonly known as MAV, is a miniature aircraft that has been gaining interest in the industry. MAV is defined as a flying platform with 15cm wingspan and operates at a speed of around 10m/s. Recently, MAV has been exposed with the latest development and link towards the biologically-inspired designs such as morphing wing. Twist morphing wing is one of the latest MAV wing design developments. The application of Twist Morphing (TM) on MAV wing has been previously known to produce better aerodynamic performance. Previous study in washin TM wing has shown a promising pos

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Zhu, Xiao-Jun, and Feng Li. "Exploration on application of dredging thermal protection in the leading edge of the wing." International Journal of Modern Physics B 34, no. 14n16 (2020): 2040105. http://dx.doi.org/10.1142/s0217979220401050.

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Aiming at the severe aerodynamic heating problem in the leading edge of the hypersonic vehicle, in order to ensure the sharp shape of the leading edge of the wing, a dredging thermal protection structure is proposed, and the built-in high-temperature heat pipe structure is used to provide thermal protection for the leading edge of the wing. By means of numerical simulation and arc wind tunnel test, the dredging thermal protection structure of the leading edge of the wing is analyzed, and the thermal protection effect of the built-in high-temperature heat pipe is obtained. The numerical results

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30

Pan, Chun Xiang, Xiao Yan Qi, Guang Zhao, and Xu Zhuo Guo. "The Test and Analysis of Nano Mechanical Properties for Dragonfly Wing." Applied Mechanics and Materials 574 (July 2014): 271–74. http://dx.doi.org/10.4028/www.scientific.net/amm.574.271.

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nanomechanical testing system in this paper has been applied to get elastic modulus and hardness of dragonfly wing, and showing their gradient changes along the wing, and also analyzing the mechanical properties in nanodimension. It is significant to make a further research for specific biological functions of dragonfly wing.

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31

Liu, Yang, Pan Zeng, and Li Ping Lei. "Experimental Study on the Stability Properties of Different Design of Tandem Wing Airship Models." Applied Mechanics and Materials 457-458 (October 2013): 1611–14. http://dx.doi.org/10.4028/www.scientific.net/amm.457-458.1611.

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This paper introduces a set of new design for the tandem wing airship, which the angular position between the front wing and tail wing are at 0o and 45o. Through the Wind Tunnel Platform test on the scaled models, lift-drag force for each configuration at different speed and mooring point was obtained and the aerodynamic performance and stability properties were analyzed. The results indicate that the tandem wing models have considerable higher aerodynamic characteristic and maintain a better stabilizability. The effect on longitudinal and yaw moment are relating to the mooring point, angle an

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32

Kulhánek, Robert. "Identification of a degradation of aerodynamic characteristics of a paraglider due to its flexibility from flight test." Aircraft Engineering and Aerospace Technology 91, no. 6 (2019): 873–79. http://dx.doi.org/10.1108/aeat-06-2018-0162.

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Purpose Aerodynamics of paragliders is very complicated aeroelastic phenomena. The purpose of this work is to quantify the amount of aerodynamic drag related to the flexible nature of a paraglider wing. Design/methodology/approach The laboratory testing on scaled models can be very difficult because of problems in the elastic similitude of such a structure. Testing of full-scale models in a large facility with a large full-scale test section is very expensive. The degradation of aerodynamic characteristics is evaluated from flight tests of the paraglider speed polar. All aspects of the identif

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Xu, Xin, Dawei Liu, Keming Cheng, and Dehua Chen. "Design and experimental validation of a specialized pressure-measuring rake for blended wing body aircraft’s unconventional inner flow channel." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 234, no. 15 (2020): 2186–96. http://dx.doi.org/10.1177/0954410020938971.

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The internal drag of the unconventional inner flow channel of blended wing body aircraft must be measured accurately to correct the air intake effect of the blended wing body flow-through model in wind tunnel tests. In this study, the pressure distribution of the inner flow channel under the interaction of internal and external flows was obtained through numerical simulation. A specialized pressure-measuring rake was designed based on the numerical results, and a validation test was conducted in a 2.4 m × 2.4 m transonic wind tunnel. Compared with the flow in traditional inlets/nozzles, the fl

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Yuan, Yan, and Le Cao. "Design of New Double-Wing Product Drop Test Machine." Applied Mechanics and Materials 608-609 (October 2014): 206–9. http://dx.doi.org/10.4028/www.scientific.net/amm.608-609.206.

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In order to simulate the free-fall motion of package, a new double-wing product drop test machine was designed. The lifting motion of the test bed was realized by the cooperation between rolling screw and stepping motor, while the opening and closing of double wing was realized by the coordinating transmission of guide rail and lead screw pair. Compared to similar products sold in the market, the new double-wing product drop test machine is low in cost, simple in structure, convenient in processing, stable in performance and beautiful in appearance. It can satisfy the demands of packing compan

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Curtis, David H., Mark F. Reeder, Craig E. Svanberg, Richard G. Cobb, and Gregory H. Parker. "Flapping Wing Micro Air Vehicle Bench Test Setup." International Journal of Micro Air Vehicles 4, no. 1 (2012): 51–77. http://dx.doi.org/10.1260/1756-8293.4.1.51.

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Iyas, Mahzan Muhammad, Muhamad Sallehuddin, Mat Ali Mohamed Sukri, and Mansor Mohd Shuhaimi. "Wind Tunnel Testing of Composite Wing Flutter Speed due to Control Surface Excitation." Applied Mechanics and Materials 315 (April 2013): 359–63. http://dx.doi.org/10.4028/www.scientific.net/amm.315.359.

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Flutter is a dynamic instability problem represents the interaction among aerodynamic forces and structural stiffness during flight. The study was conducted to investigate whether deflecting the control surface will affect the flutter speed and the flutter frequency. A wind tunnel test was performed using a flat plate wing made of composite material. It was found that by deflecting the control surface at 45°, the wing entered flutter state at wind speed of 28.1 m/s instead of 33.4 m/s. In addition, the flutter frequency also reduced from 224.52 Hz to 198.96 Hz. It was concluded that by deflect

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Pak, Chan-gi, and Shun-fat Lung. "Flutter Analysis of Aerostructures Test Wing with Test Validated Structural Dynamic Model." Journal of Aircraft 48, no. 4 (2011): 1263–72. http://dx.doi.org/10.2514/1.c031257.

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38

Lu, Bo, Bin Bin Lv, Li Yu, Hong Tao Guo, Yu Yan, and Xi Ping Kou. "Design and Application of an all Moving Wing Model Limiting and Locking Device." Advanced Materials Research 753-755 (August 2013): 1031–34. http://dx.doi.org/10.4028/www.scientific.net/amr.753-755.1031.

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To effectively excite the all moving wing flutter model and limiting or quick locking model in case of bigger amplitude of the model, an excitation and limiting and locking device is designed for the high-speed wind tunnel flutter test model. This paper introduces the structure arrangement, control principle and strategy of this device. The wind tunnel flutter test indicates that this device can enhance the SNR of the test data, improve the boundary prediction precision of flutter, prevent the model from entering the flutter divergence state and protect the model and wind tunnel test equipment

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Syaifuddin, Moh, Hoon Cheol Park, Kwang Joon Yoon, and Nam Seo Goo. "Design and Test of Flapping Device Mimicking Insect Flight." Key Engineering Materials 306-308 (March 2006): 1163–68. http://dx.doi.org/10.4028/www.scientific.net/kem.306-308.1163.

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This paper addresses detail design and demonstration of an insect-mimicking flappingwing mechanism composed of LIPCA (Lightweight Piezo-Composite Actuator) and linkage system that can amplify the actuation displacement of LIPCA. The angular amplification of the linkage system can provide various flapping angles by adjusting the actuation point of the LIPCA. The device can generate flapping frequency ranging from 5 to 50 Hz depending on weight of the wing and linkages. Flapping tests using different wing mass, area, and aspect ratio were performed to investigate the flapping performance. The te

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YAMAMOTO, Kohei, and Osamu KOBAYASHI. "1204 Wind Tunnel Test on Lift-Drag Characteristics of Wing in Formation Flight." Proceedings of Conference of Hokuriku-Shinetsu Branch 2014.51 (2014): _1204–1_—_1204–2_. http://dx.doi.org/10.1299/jsmehs.2014.51._1204-1_.

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Liu, Yi, Changchuan Xie, Chao Yang, and Jialin Cheng. "Gust response analysis and wind tunnel test for a high-aspect ratio wing." Chinese Journal of Aeronautics 29, no. 1 (2016): 91–103. http://dx.doi.org/10.1016/j.cja.2015.12.013.

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Hu, Yi Huai, Xiang Ming Zeng, and Song Yue Li. "Research on the Aerodynamic Characteristics of Ellipse Wing Sail." Advanced Materials Research 347-353 (October 2011): 2249–54. http://dx.doi.org/10.4028/www.scientific.net/amr.347-353.2249.

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A kind of novel airfoil sail is proposed in this paper based on the research of traditional arc wing sails. The aerodynamic characteristic- the lift coefficient and drag coefficient is numerically calculated with FLUENT 6.0 and the results are verified by wind tunnel test. It is proved that the aerodynamic characteristic of the novel sail is much better than the arc wing sail.

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Ouyang, Yan, Kaichun Zeng, Xiping Kou, Yingsong Gu, and Zhichun Yang. "Experimental and Numerical Studies on Static Aeroelastic Behaviours of a Forward-Swept Wing Model." Shock and Vibration 2021 (June 10, 2021): 1–12. http://dx.doi.org/10.1155/2021/5535192.

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The static aeroelastic behaviours of a flat-plate forward-swept wing model in the vicinity of static divergence are investigated by numerical simulations and wind tunnel tests. A medium fidelity model based on the vortex lattice method (VLM) and nonlinear structural analysis is proposed to calculate the displacements of the wing structure with large deformation. Follower forces effect and geometric nonlinearity are considered to calculate the deformation of the wing by finite element method (FEM). In the wind tunnel tests, the divergence dynamic pressure is predicted by the Southwell method, a

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Wada, Daichi, and Masato Tamayama. "Wing Load and Angle of Attack Identification by Integrating Optical Fiber Sensing and Neural Network Approach in Wind Tunnel Test." Applied Sciences 9, no. 7 (2019): 1461. http://dx.doi.org/10.3390/app9071461.

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The load and angle of attack (AoA) for wing structures are critical parameters to be monitored for efficient operation of an aircraft. This study presents wing load and AoA identification techniques by integrating an optical fiber sensing technique and a neural network approach. We developed a 3.6-m semi-spanned wing model with eight flaps and bonded two optical fibers with 30 fiber Bragg gratings (FBGs) each along the main and aft spars. Using this model in a wind tunnel test, we demonstrate load and AoA identification through a neural network approach. We input the FBG data and the eight fla

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Hainsworth, F. Reed. "Wing movements and positioning for aerodynamic benefit by Canada geese flying in formation." Canadian Journal of Zoology 67, no. 3 (1989): 585–89. http://dx.doi.org/10.1139/z89-084.

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Wing tip spacing (the distance between wing tips of adjacent birds at maximum span, perpendicular to the flight path), depth (distance between adjacent birds along the flight path), wing beat frequencies, and extreme relative wing positions were measured for Canada geese (Branta canadensis) flying in V formations to test for use of variation in trailing wing tip vortex positions produced by wing movements. Use of vertical vortex position variation requires similarity in wing beat frequency. An average of only 48% of 73 birds in eight formations had frequencies similar to those of the bird ahea

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., Sutrisno, Febryanto Nugroho, Yogi Adi Pratama, Sigit Iswahyudi, and Setyawan Bekti Wibowo. "Sukhoi SU-47 Berkut and Eurofighter Typhoon Models Flow Visualization and Performance Investigation Using GAMA Water Tunnel." Modern Applied Science 13, no. 2 (2019): 21. http://dx.doi.org/10.5539/mas.v13n2p21.

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Changes and modifications to the wings of fighter aircraft were carried out, one of which was the forward swept wing which was a moderate wing that continues to develop. There were also types of delta wings that had been applied to many fighter planes. Both types of aircraft wings had certainly different aerodynamic characteristics. This research would study the flow visualization that occurs in the aircraft model body to determine the aerodynamic characteristics of the forward swept wing and delta wing. This study used a water tunnel to observe the aerodynamic flow and forces that occurred in

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Hua, Xin, Wei Shao, Chun Hua Zhang, and Zhi Qiang Zhang. "Based on Imitation Seagull Airfoil UVA Wing Numerical Simulation." Applied Mechanics and Materials 271-272 (December 2012): 791–96. http://dx.doi.org/10.4028/www.scientific.net/amm.271-272.791.

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Wing aircraft is one of the major components to generate lift, in today's energy shortage, design the high lift-to-drag ratio wing is the goal pursued by, The author in the exploration of bionic airfoil aerodynamic characteristics on the basis of, which will be applied to straight wing design so as to improve the aerodynamic performance of aircraft.Our research mainly includes two aspects: first, the use of imitation seagull airfoil and NACA4412 airfoil are designed into the straight wing. The use of FLUENT software in Re=300000condition carries on the numerical simulation results show that th

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Phillips, Nathan, Kevin Knowles, and Richard J. Bomphrey. "Petiolate wings: effects on the leading-edge vortex in flapping flight." Interface Focus 7, no. 1 (2017): 20160084. http://dx.doi.org/10.1098/rsfs.2016.0084.

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The wings of many insect species including crane flies and damselflies are petiolate (on stalks), with the wing planform beginning some distance away from the wing hinge, rather than at the hinge. The aerodynamic impact of flapping petiolate wings is relatively unknown, particularly on the formation of the lift-augmenting leading-edge vortex (LEV): a key flow structure exploited by many insects, birds and bats to enhance their lift coefficient. We investigated the aerodynamic implications of petiolation P using particle image velocimetry flow field measurements on an array of rectangular wings

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Mikhalyov, Semyon, Andrey Dunaevsky, Leonid Teperin, Roman Vasilyev, and Andrey Redkin. "Effects of Propeller Slipstream of Distributed Electric Propulsion on the Wing-Flap System." MATEC Web of Conferences 304 (2019): 02018. http://dx.doi.org/10.1051/matecconf/201930402018.

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The studies are aimed at investigating the mechanism to ensure the high lift by installing propellers in front of the wing and using interference effects. The model of the wing section of a regional STOL aircraft with DEPSis considered. The wing section is equipped with a trailing edge device (Fowler flap) and DEPS consisting of motors with propellers. Parametric and experimental studies of the interaction between DEPS propellers and the regional STOL aircraft wing-flap system were carried out. The development and verification of aerodynamic calculation method for the wing section at low Reyno

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Hart, K., and M. Bienz. "A test for cell autonomy, based on di-cistronic messenger translation." Development 122, no. 3 (1996): 747–51. http://dx.doi.org/10.1242/dev.122.3.747.

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We have devised a test for cell autonomy of a gene that is switched on ectopically in a clone of cells, allowing us to ask whether the wild-type activity of this gene can influence neighbouring cells. To switch on the test gene, we used the yeast FRT system, and marked the FRT-generated cell clone by co-expressing beta-galactosidase. Co-expression is achieved by a stretch of 5′ untranslated mRNA from the homeotic gene Ultrabithorax (Ubx), which is inserted between the two coding sequences. We show that this Ubx sequence mediates efficient and reliable di-cistronic mRNA translation in wing imag

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