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Journal articles on the topic 'Wing test'

Author: Grafiati

Published: 28 June 2021

Last updated: 29 July 2025

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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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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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6

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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7

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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8

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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11

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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12

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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13

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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14

Du, Siliang, Yi Zha, and Qijun Zhao. "Research on Aerodynamic Test Validation and the Vector Force Control Method for an E-STOL Fan Wing Unmanned Aerial Vehicle." Aerospace 11, no. 1 (2024): 55. http://dx.doi.org/10.3390/aerospace11010055.

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The concept of the Fan Wing, a novel aircraft vector-force-integrated device that combines a power unit with a fixed wing to generate distributed lift and thrust by creating a low-pressure vortex on the wing’s surface, was studied. To investigate the unique propulsion mechanism of the Fan Wing, a Fan Wing test platform was developed, and experiments were conducted in a wind tunnel. At the same time, numerical simulations were established. In order to further improve the aerodynamic efficiency of the Fan Wing and decouple the control of lift and thrust, an improved scheme for the leading-edge s

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15

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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16

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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17

Yusoff, Hamid, Noor Iswadi Ismail, Muhammad Reedzman Mohd Rakmi, Shafiq Suhaimi, and Wirachman Wisnoe. "Lift Generation of Compliant Wing Mechanism of Flapping Wing." International Journal of Engineering & Technology 7, no. 4.25 (2018): 93–98. http://dx.doi.org/10.14419/ijet.v7i4.25.22404.

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Flapping wing micro air vehicles are small, lightweight and can fly in a low Reynolds Number environment. They are capable of flying at low Reynolds number environment with amazing agility by imitating natural flyers like bats and have compliant wings while flapping. The primary goal of this study is to design and fabricate the compliant mechanism of flapping wing for improvement of lift performance of a MAV. The test was carried out in an open-air wind tunnel. Furthermore, the compliant wing mechanism is measured based on Angle of attack, Reynolds number and flapping frequency. The result sho

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18

Qu, Xiyao, Zijing Liu, Baiyang Yu, Wei An, Xuejun Liu, and Hongqiang Lyu. "Predicting pressure coefficients of wing surface based on the transfer of spatial dependency." AIP Advances 12, no. 5 (2022): 055225. http://dx.doi.org/10.1063/5.0093144.

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Multi-conditional holographic pressure coefficients over a wing are crucial for wing design, and a wind tunnel test is an indispensable means to obtain this profile. However, it is resource-consuming to obtain wind tunnel data under different conditions and only a limited number of sensors can be placed on the wing model during one test, which results in sparse pressure coefficient data with distribution inconsistency across cross sections and conditions. Thus, how to obtain pressure coefficients of more cross sections or even the whole wing surface with multiple conditions from the distributi

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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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20

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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21

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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22

Sabari Vihar, R., J. V. M. Lal Jeyan, and K. Sai Priyanka. "Experimental Flutter Analysis over Different Selected Wing Planforms by Varying the Wing Cross Section Geometry." ACS Journal for Science and Engineering 3, no. 2 (2023): 52–60. http://dx.doi.org/10.34293/acsjse.v3i2.85.

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Flutter is a phenomenon that occurs in structures which are subjected to aerodynamic forces. As the wing model flies at increasing speeds and increasing angle of attack the vibrations get increased and the frequency of these modes coincide with each other which leads to resonance, this is called Flutter and this may lead to catastrophic failures in the aircraft flight. An appropriate wing model design includes various parameters that need to be selected according to the wind-tunnel test conditions. The material used for skin is monocot, spars are made of aluminium, ribs are made of balsa wood.

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23

Li, Xing, Wei Qian, Ling Xiao, Xinyu Ai, and Jun Liu. "Optimized Design and Test of Geometrically Nonlinear Static Aeroelasticity Model for High-Speed High-Aspect-Ratio Wing." Aerospace 11, no. 12 (2024): 1015. https://doi.org/10.3390/aerospace11121015.

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Large transport aircraft tend to adopt a wing layout with a high aspect ratio and swept-back angle due to the requirement of a high lift-to-drag ratio. Composite material is typically employed to ensure the light weight of the structure, causing serious static aeroelasticity problems to the aircraft. When the airplane is flying in the transonic region, its aerodynamic load is very complex, and the large load leads to large deformation of the wing, triggering geometric nonlinear effects, which further affects the static aerodynamic elasticity characteristics of the wing. In this study, in order

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Mahbubur, Rahman, Ali Mohammad, and Mostofa Hossain Md. "An Experimental Investigation of the Effect of Aspect Ratio on the Airfoil Characteristics of NACA 0012 Wing." Advancement in Mechanical Engineering and Technology 3, no. 3 (2020): 1–15. https://doi.org/10.5281/zenodo.4068002.

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<em>The aspect ratio has a great effect on the aerodynamic characteristics. It is an important technique for the improvement of aerodynamic performance through drag reduction. The effect of aspect ratio on the airfoil performance is investigated about axially symmetric wings as a function of the angle of attack. Optimum design of lifting surface provides maximum possible lift force and minimum possible drag force. The wind tunnel used for the experiments is an open conduit and has a 1200x1200 mm2 x-section with a closed test chamber. Three different types of airfoil with different aspect ratio

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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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26

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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27

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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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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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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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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Yugal, Krishna Shrestha, Kawar Yubraj, Dhakal Saman, and Bhattarai Aayush. "Development of Flow Visualization and Instrumentation Systems for Open Circuit Subsonic Wind Tunnel and Their Validation with Experiments on NACA 0012 Airfoil." Journal of Recent Trends in Mechanics 5, no. 1 (2020): 20–41. https://doi.org/10.5281/zenodo.3768214.

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This report describes the flow visualization and instrumentation systems developed for open circuit subsonic wind tunnel. First off, suitable setup for mounting wing section inside the test section along with load cells for measuring lift and drag was designed and fabricated. Numerical simulation was done prior to experimentation on wing section of NACA 0012 airfoil geometry. Thereafter, flow visualization of flow over the said wing section was done using commercially available smoke generator, smoke fluid, and 5V, 515-532 nm LASER.  A wind tunnel test was carried out for the wing section

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Desai, Siddhant, Joseph A. Schetz, Rakesh K. Kapania, and Rikin Gupta. "Wind Tunnel Testing of Tethered Inflatable Wings." Journal of Aircraft 61, no. 6 (2024): 1717–34. https://doi.org/10.2514/1.c037437.

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A wind tunnel testing approach for tethered inflatable wings is presented. Use cases for such wings range from airborne wind energy systems to high-altitude communication platforms. The tests were conducted for two tethered inflatable wings, one made out of nylon fabric and the other an ultra-high-molecular-weight polyethylene fabric. They were tested within a speed range of 15–32.5 m/s for three tether attachment configurations. Stereo photogrammetry data, force and moment measurements, and wake pressure measurements were recorded for each speed and test configuration. These measurements prov

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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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Yusoff, H., M. R. Arifin, N. S. Shaari, et al. "Lift and Drag Performance Based on Varying Flapping Wing Camber at Low Reynolds Number of Micro Air Vehicles (MAVs)." Journal of the Society of Automotive Engineers Malaysia 5, no. 3 (2021): 348–54. http://dx.doi.org/10.56381/jsaem.v5i3.177.

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   Flapping-Wing Micro Air Vehicles (FW-MAVs) are small hand-held flying vehicles that can maneuver in constrained space owing to their lightweight, low aspect ratio and the ability to fly in a low Reynolds number environment. In this study, the aerodynamic characteristics such as time-averaged lift (CL avg) and time-averaged drag (CD avg) of camber wings with different five wind tunnel test models with 6, 9, 12, and 15 per cent camber were developed and the results were compared with a flat wing to assess the effects of camber wing on the aerodynamic performance for flapping

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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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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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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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Niu, Zhong-Guo, Xiang-Hui Xu, Jian-Feng Wang, Jia-Li Jiang, and Hua Liang. "Experiment on longitudinal aerodynamic characteristics of flying wing model with plasma flow control." Acta Physica Sinica 71, no. 2 (2022): 024702. http://dx.doi.org/10.7498/aps.71.20211425.

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Horizontal tail is eliminated from the flying wing layout for improving the low observable and aerodynamic efficiency, resulting in degrading longitudinal maneuverability and fight stability. The low speed wind tunnel test study of improving the longitudinal aerodynamic characteristics of large aspect ratio flying wing model is carried out by using plasma flow control technology. The flying wing model has a leading-edge sweep angle of 34.5° and an aspect ratio of 5.79. The reasons for deteriorating the static maneuverability and stability of the flying wing model and the mechanism of plasma co

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Bi, Yanqiang, Wen Gao, Chao Fan, Zhihai Xiang, and Chunlin Du. "Experimental study on thermally induced vibration of flexible solar cell wing simulator." Journal of Physics: Conference Series 2882, no. 1 (2024): 012068. http://dx.doi.org/10.1088/1742-6596/2882/1/012068.

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Abstract With the development of large spacecraft and satellite payloads, the power supply required is increasing, especially in space solar power stations, and the large flexible solar wing is an inevitable trend in the future. Due to their light weight and large area, flexible solar wings may face thermally induced vibration during orbit operation, which will lead to the degradation of spacecraft performance and even structural damage. In this paper, the test method of a flexible solar wing simulator is established, and the thermally induced vibration test of a flexible solar cell wing simul

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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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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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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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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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Laguna-Canales, Aldo Saul, Guillermo Urriolagoitia-Sosa, Beatriz Romero-Ángeles, et al. "Mechanical Design and Numerical Analysis of a New Front Wing for a Formula One Vehicle." Fluids 8, no. 7 (2023): 210. http://dx.doi.org/10.3390/fluids8070210.

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In motorsports, the correct design of every device that constitutes a vehicle is a significant task for engineers because the car’s efficiency on the track depends on making it competitive. However, the physical integrity of the pilot is also at stake, since a bad vehicle design can cause serious mishaps. To achieve the correct development of a front wing for a single-seater vehicle, it is necessary to adequately simulate the forces that are generated on a car to evaluate its performance, which depends on the aerodynamic forces of the front wing that are present due to its geometry. This work

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Rahman, Fahmi Izzuddin Abdul, Shabudin Mat, Nor Haizan Mohamed Radzi, Mohd Nazri Mohd Nasir, and Roselina Sallehudin. "Identification of Sharp Edge Non-Slender Delta Wing Aerodynamic Coefficient Using Neural Network." Journal of Physics: Conference Series 2129, no. 1 (2021): 012086. http://dx.doi.org/10.1088/1742-6596/2129/1/012086.

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Abstract Delta wing formed a vortical flow on its surface which produced higher lift compared to conventional wing. The vortical flow is complex and non-linear which requires more studies to understand its flow physics. However, conventional flow analysis (wind tunnel test and computational flow dynamic) comes with several significant drawbacks. In recent times, application of neural network as alternative to conventional flow analysis has increased. This study is about utilization of Multi-Layer Perceptron (MLP) neural network to predict the coefficient of pressure (Cp ) on a delta wing model

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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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Riskin, Daniel K., José Iriarte-Díaz, Kevin M. Middleton, Kenneth S. Breuer, and Sharon M. Swartz. "The effect of body size on the wing movements of pteropodid bats, with insights into thrust and lift production." Journal of Experimental Biology 213, no. 23 (2010): 4110–22. https://doi.org/10.5281/zenodo.13433100.

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(Uploaded by Plazi for the Bat Literature Project) In this study we compared the wing kinematics of 27 bats representing six pteropodid species ranging more than 40 times in body mass (Mb0.0278–1.152kg), to determine whether wing posture and overall wing kinematics scaled as predicted according to theory. The smallest species flew in a wind tunnel and the other five species in a flight corridor. Seventeen kinematic markers on the midline and left side of the body were tracked in three dimensions. We used phylogenetically informed reduced major axis regression to test for allometry. We found

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Riskin, Daniel K., José Iriarte-Díaz, Kevin M. Middleton, Kenneth S. Breuer, and Sharon M. Swartz. "The effect of body size on the wing movements of pteropodid bats, with insights into thrust and lift production." Journal of Experimental Biology 213, no. 23 (2010): 4110–22. https://doi.org/10.5281/zenodo.13433100.

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(Uploaded by Plazi for the Bat Literature Project) In this study we compared the wing kinematics of 27 bats representing six pteropodid species ranging more than 40 times in body mass (Mb0.0278–1.152kg), to determine whether wing posture and overall wing kinematics scaled as predicted according to theory. The smallest species flew in a wind tunnel and the other five species in a flight corridor. Seventeen kinematic markers on the midline and left side of the body were tracked in three dimensions. We used phylogenetically informed reduced major axis regression to test for allometry. We found

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