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Journal articles on the topic 'Thin Cambered Airfoil'

Author: Grafiati

Published: 4 June 2021

Last updated: 1 February 2022

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1

Ali, Nesar, Mostafizur Rahman Komol, and Mohammad Takiuddin Saki. "Study on Thin Airfoil Theory & Performance Test of Elliptical Wing as Compared to Model Mosquito Wing and NACA 64A012 Mod Airfoil." European Journal of Engineering Research and Science 3, no. 4 (2018): 48. http://dx.doi.org/10.24018/ejers.2018.3.4.665.

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Thin airfoil theory is a simple conception of airfoils that describes angle of attack to lift for incompressible, inviscid flows. It was first devised by famous German-American mathematician Max Munk and therewithal refined by British aerodynamicist Hermann Glauertand others in the 1920s. The thin airfoil theory idealizes that the flow around an airfoil as two-dimensional flow around a thin airfoil. It can be conceived as addressing an airfoil of zero thickness and infinite wingspan. Thin airfoil theory was particularly citable in its day because it provided a well-established theoretical basi

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2

Wang, Meng, Stephane Moreau, Gianluca Iaccarino, and Michel Roger. "LES Prediction of Wall-Pressure Fluctuations and Noise of a Low-Speed Airfoil." International Journal of Aeroacoustics 8, no. 3 (2009): 177–97. http://dx.doi.org/10.1260/147547208786940017.

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This paper discusses the prediction of wall-pressure fluctuations and noise of a low-speed flow past a thin cambered airfoil using large-eddy simulation (LES). The results are compared with experimental measurements made in an open-jet anechoic wind-tunnel at Ecole Centrale de Lyon. To account for the effect of the jet on airfoil loading, a Reynolds-averaged Navier-Stokes calculation is first conducted in the full wind-tunnel configuration, and the mean velocities from this calculation are used to define the boundary conditions for the LES in a smaller domain within the potential core of the j

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3

Shi, Xing, Xianwen Huang, Yao Zheng, and Susu Zhao. "Effects of cambers on gliding and hovering performance of corrugated dragonfly airfoils." International Journal of Numerical Methods for Heat & Fluid Flow 26, no. 3/4 (2016): 1092–120. http://dx.doi.org/10.1108/hff-10-2015-0414.

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Purpose – The purpose of this paper is to explore the effects of the camber on gliding and hovering performance of two-dimensional corrugated airfoils. While the flying mechanism of natural flyers remains a myth up to nowadays, the simulation serves as a minor step toward understanding the steady and unsteady aerodynamics of the dragonfly flight. Design/methodology/approach – The lattice Boltzmann method is used to simulate the flow past the cambered corrugated dragonfly airfoil at low Reynolds numbers. For gliding flight, the maximum camber, the distance of the location of maximum camber poin

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4

Maleki Dastjerdi, Sajad, Kobra Gharali, Armughan Al-Haq, and Jatin Nathwani. "Application of Simultaneous Symmetric and Cambered Airfoils in Novel Vertical Axis Wind Turbines." Applied Sciences 11, no. 17 (2021): 8011. http://dx.doi.org/10.3390/app11178011.

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Two novel four-blade H-darrieus vertical axis wind turbines (VAWTs) have been proposed for enhancing self-start capability and power production. The two different airfoil types for the turbines are assessed: a cambered S815 airfoil and a symmetric NACA0018 airfoil. For the first novel wind turbine configuration, the Non-Similar Airfoils 1 (NSA-1), two NACA0018 airfoils, and two S815 airfoils are opposite to each other. For the second novel configuration (NSA-2), each of the S815 airfoils is opposite to one NACA0018 airfoil. Using computational fluid dynamics (CFD) simulations, static and dynam

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5

Liao, Yan Ping, Li Liu, and Teng Long. "Investigation of Various Parametric Geometry Representation Methods for Airfoils." Applied Mechanics and Materials 110-116 (October 2011): 3040–46. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.3040.

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Abstract—This paper presents the investigation of typical parametric geometry representation methods for airfoils, namely, PARSEC method, orthogonal basis function method and CST method. The investigation assesses the fitting accuracy of these parametric methods for various airfoils including the symmetric airfoil, cambered airfoil and supercritical airfoil. The design variables of these parametric methods are solved by the methods of least squares fit. The fitting results show that the fitting accuracy of CST method is better than other parametric methods for airfoil. The aerodynamics analysi

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6

Désert, T., JM Moschetta, and H. Bézard. "Numerical and experimental investigation of an airfoil design for a Martian micro rotorcraft." International Journal of Micro Air Vehicles 10, no. 3 (2018): 262–72. http://dx.doi.org/10.1177/1756829318794171.

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The present paper aims at investigating the impact of an airfoil design on the propulsion system for a Martian rotary wing micro air vehicle. The main challenge for flying on Mars is the atmosphere’s density and speed of sound that are significantly lower than on Earth. It leads to compressible ultra-low Reynolds number ([Formula: see text]) flows for a coaxial rotorcraft with a 30 cm diameter . Since those flows are unknown in the biosphere, numerical tools have not been validated yet. Therefore, the test section from a known depressurized experiment is simulated in 3D for solver assessment.

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7

Gao, Ji, Rui Shan Yuan, Ming Hui Zhang, and Yong Hui Xie. "Numerical Study on Thrust Generation Performance of Plunging Airfoils." Applied Mechanics and Materials 312 (February 2013): 235–38. http://dx.doi.org/10.4028/www.scientific.net/amm.312.235.

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In this paper, the effects of angle of attack, camber and camber location on propulsion performance of flapping airfoils undergoing plunging motion were numerically studied at Re=20000 and h=0.175. The unsteady incompressible viscous flow around four different airfoil sections was simulated applying the dynamic mesh. The results show that the time averaged thrust coefficient CTmean and propulsive efficiency η of the symmetric airfoil decrease with the increasing angle of attack, and the variation of CTmean is more obvious than that of CPmean. Both CTmean and η for NACA airfoils studied in this

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8

Sunada, Shigeru, Akitoshi Sakaguchi, and Keiji Kawachi. "Airfoil Section Characteristics at a Low Reynolds Number." Journal of Fluids Engineering 119, no. 1 (1997): 129–35. http://dx.doi.org/10.1115/1.2819098.

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The aerodynamic characteristics of airfoils operating at Re = 4 × 103 were examined, varying the parameters related to the airfoil shape such as thickness, camber, and roughness. Airfoils with good aerodynamic performance at this Re have the following shape characteristics: (1) they are thinner than airfoils for higher Re numbers, (2) they have a sharp leading edge, and (3) they have a camber of about five percent with its maximum camber at about mid-chord. The characteristics of airfoils are strongly affected by leading edge vortices. The measured two-dimensional airfoil characteristics indic

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9

Knight, Jason, Simon Fels, Benjamin Beazley, George Haritos, and Andrew Lewis. "Fluid–Structure Interaction of Symmetrical and Cambered Spring-Mounted Wings Using Various Spring Preloads and Pivot Point Locations." Applied Mechanics 2, no. 3 (2021): 591–612. http://dx.doi.org/10.3390/applmech2030034.

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The fluid–structure interaction of a pivoting rigid wing connected to a spring and subjected to freestream airflow in a wind tunnel is presented. Fluid–structure interactions can, on the one hand, lead to undesirable aerodynamic behaviour or, in extreme cases, to structural failure. On the other hand, improved aerodynamic performance can be achieved if a controlled application within certain limitations is provided. One application is the reduction of drag of road vehicles at higher speeds on a straight, while maintaining downforce at lower speeds during cornering. Conversely, another applicat

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10

Cole, Julian D., and Norman D. Malmuth. "Wave drag due to lift for transonic airplanes." Proceedings of the Royal Society A: Mathematical, Physical and Engineering Sciences 461, no. 2054 (2005): 541–60. http://dx.doi.org/10.1098/rspa.2004.1376.

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Lift–dominated pointed aircraft configurations are considered in the transonic range. To make the approximations more transparent, two–dimensionally cambered untwisted lifting wings of zero thickness with aspect ratio of order one are treated. An inner expansion, which starts as Jones's theory, is matched to a nonlinear outer transonic theory as in Cheng and Barnwell's earlier work. To clarify issues, minimize ad hoc assumptions existing in earlier studies, as well as provide a systematic expansion scheme, a deductive rather than inductive approach is used with the aid of intermediate limits a

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11

Lee, Seongkyu. "The Effect of Airfoil Shape on Trailing Edge Noise." Journal of Theoretical and Computational Acoustics 27, no. 02 (2019): 1850020. http://dx.doi.org/10.1142/s2591728518500202.

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This paper investigates the effect of airfoil shape on trailing edge noise. The boundary layer profiles are obtained by XFOIL and the trailing edge noise is predicted by a TNO semi-empirical model. In order to investigate the noise source characteristics, the wall pressure spectrum is decomposed into three components. This decomposition helps in finding the dominant source region and the peak noise frequency for each airfoil. The method is validated for a NACA0012 airfoil, and then five additional wind turbine airfoils are examined: NACA0018, DU96-w-180, S809, S822 and S831. It is found that t

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12

Rahi, Abbas, Mortaza Shahravi, and Darvish Ahmadi. "The Effects of Airfoil Camber on Flutter Suppression Regarding Timoshenko Beam Theory." Applied Mechanics and Materials 110-116 (October 2011): 1531–38. http://dx.doi.org/10.4028/www.scientific.net/amm.110-116.1531.

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The application of Timoshenko beam theory is presented, thereby the effects of airfoil camber can be investigated analytically and numerically by considering rotary inertia and shear deformation in addition to moment of inertia, aerodynamic loading and bending/torsion coupling. Regarding a tuned blisk, the analysis is simplified to a single blade with plunge and pitch DOF. Pressure distribution of the airfoil surfaces and the resulting aerodynamic forces are calculated with ‘ANSYS/FLOTRAN’ during one-cycle time marching at several reduced frequencies. A parametric relation is then achieved by

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13

Li, Shoutu, Ye Li, Congxin Yang, et al. "Design and Testing of a LUT Airfoil for Straight-Bladed Vertical Axis Wind Turbines." Applied Sciences 8, no. 11 (2018): 2266. http://dx.doi.org/10.3390/app8112266.

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The airfoil plays an important role in improving the performance of wind turbines. However, there is less research dedicated to the airfoils for Vertical Axis Wind Turbines (VAWTs) compared to the research on Horizontal Axis Wind Turbines (HAWTs). With the objective of maximizing the aerodynamic performance of the airfoil by optimizing its geometrical parameters and by considering the law of motion of VAWTs, a new airfoil, designated the LUT airfoil (Lanzhou University of Technology), was designed for lift-driven VAWTs by employing the sequential quadratic programming optimization method. Afte

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14

Motta, Valentina, Alberto Guardone, and Giuseppe Quaranta. "Influence of airfoil thickness on unsteady aerodynamic loads on pitching airfoils." Journal of Fluid Mechanics 774 (June 11, 2015): 460–87. http://dx.doi.org/10.1017/jfm.2015.280.

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The influence of the airfoil thickness on aerodynamic loads is investigated numerically for harmonically pitching airfoils at low incidence, under the incompressible and inviscid flow approximation. Force coefficients obtained from finite-volume unsteady simulations of symmetrical 4-digit NACA airfoils are found to depart from the linear Theodorsen model of an oscillating flat plate. In particular, the value of the reduced frequency resulting in the inversion – from clockwise to counter-clockwise – of the lift/angle-of-attack hysteresis curve is found to increase with the airfoil thickness. Bo

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15

Çamur, Hüseyin, and Youssef Kassem. "Operating a Three Blade-Wind Car with Wind Energy." Advanced Materials Research 622-623 (December 2012): 1199–203. http://dx.doi.org/10.4028/www.scientific.net/amr.622-623.1199.

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Airfoils have become a combined aspect of human flight as it has evolved over the last century. As the design of each airfoil determines many aspects of its use in the real world, all significant characteristics must be analyzed prior to implementation. The aerodynamic effects of pressure, drag, lift, and pitching moment are used to evaluate the behavior of the airfoil. The airfoil shape is expressed analytically as a function of some design parameters. The NACA 0012 and NACA 2412 are used with design parameters that control the camber and the thickness of the airfoil. Singularity method is th

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16

Hou, Longfeng, Sheng Shen, and Ying Wang. "Numerical Study on Aerodynamic Performance of Different Forms of Adaptive Blades for Vertical Axis Wind Turbines." Energies 14, no. 4 (2021): 880. http://dx.doi.org/10.3390/en14040880.

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The wind energy exploitation technique has been developed very quickly in recent years. The vertical axis wind turbine is a hot research domain due to several advantages: low noise, flexible for installation, ease of maintenance, great safety and credibility, etc. The aerodynamic performances of different forms of airfoils including an active deformation airfoil and a fluid-solid coupling passive airfoil with two-dimensional (2D) and three-dimensional (3D) cases have been investigated numerically in this paper. Firstly, the aerodynamic performances of the airfoils with the maximum deformation

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17

Hsieh, W. C., J. M. Miao, C. C. Lai, and C. S. Tai. "Wind Tunnel Analysis on Performance of H-Rotor VAWTs with NACA 64xx Blades." Advanced Materials Research 488-489 (March 2012): 1213–18. http://dx.doi.org/10.4028/www.scientific.net/amr.488-489.1213.

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The purpose of this study was to explore the effects of wind speed, airfoil thickness and setting angle of blades on the output performance of a VAWT system. Three shapes of the blades as NACA6422, NACA6412, and NACA6404 were fabricated and installed in the support mechanism to test the effect of airfoil thickness on the output performance. Results indicated that the section shape of blade with a cambered NACA 64XX series is prior to the ordinary symmetric NACA0022 series used in VAWT systems. The statistic analysis showed that the contribution of setting angle on the output performance is 12.

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18

Zhang, Qiang, Matt Goodro, Phillip M. Ligrani, Ricardo Trindade, and Sri Sreekanth. "Influence of Surface Roughness on the Aerodynamic Losses of a Turbine Vane." Journal of Fluids Engineering 128, no. 3 (2005): 568–78. http://dx.doi.org/10.1115/1.2175163.

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The effects of surface roughness on the aerodynamic performance of a turbine vane are investigated for three Mach number distributions, one of which results in transonic flow. Four turbine vanes, each with the same shape and exterior dimensions, are employed with different rough surfaces. The nonuniform, irregular, three-dimensional roughness on the tested vanes is employed to match the roughness which exists on operating turbine vanes subject to extended operating times with significant particulate deposition on the surfaces. Wake profiles are measured for two different positions downstream t

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19

Bogdanowicz, Włodzimierz, Jacek Krawczyk, Robert Paszkowski, and Jan Sieniawski. "Primary Crystal Orientation of the Thin-Walled Area of Single-Crystalline Turbine Blade Airfoils." Materials 12, no. 17 (2019): 2699. http://dx.doi.org/10.3390/ma12172699.

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The thin-walled airfoil areas of as-cast single-crystalline turbine blades made of CMSX-4 superalloy were studied. The blades were produced by the industrial Bridgman technique at withdrawal rates of 2, 3 and 4 mm/min. The angle between the [001] crystallographic direction and blade axis, related to the primary orientation, was defined by the Ω-scan X-ray diffraction method at points on the camber line located near the tip of an airfoil and at points of a line located in parallel and near the trailing edge. Additionally, primary crystal orientation was determined by Laue diffraction at the sel

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20

He, W., R. S. Gioria, J. M. Pérez, and V. Theofilis. "Linear instability of low Reynolds number massively separated flow around three NACA airfoils." Journal of Fluid Mechanics 811 (December 15, 2016): 701–41. http://dx.doi.org/10.1017/jfm.2016.778.

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Two- and three-dimensional modal and non-modal instability mechanisms of steady spanwise-homogeneous laminar separated flow over airfoil profiles, placed at large angles of attack against the oncoming flow, have been investigated using global linear stability theory. Three NACA profiles of distinct thickness and camber were considered in order to assess geometry effects on the laminar–turbulent transition paths discussed. At the conditions investigated, large-scale steady separation occurs, such that Tollmien–Schlichting and cross-flow mechanisms have not been considered. It has been found tha

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21

Zhu, Chengyong, and Tongguang Wang. "Comparative Study of Dynamic Stall under Pitch Oscillation and Oscillating Freestream on Wind Turbine Airfoil and Blade." Applied Sciences 8, no. 8 (2018): 1242. http://dx.doi.org/10.3390/app8081242.

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This study aims to assess the dynamic stall of the wind turbine blade undergoing pitch oscillation (PO) and oscillating freestream (OF), respectively. Firstly, a thin-airfoil theoretical analysis was performed to differentiate between these two dynamic effects. During upstroke, PO results in a positive effective airfoil camber, while OF has an additional negative effective airfoil camber, and yet in contrast during downstroke, PO decreases the effective camber, while OF increases the effective camber. Secondly, the equivalence relation between PO and OF is investigated by numerically solving t

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22

Latif, Shahid, Zhou Hong, and Muhammad Ismail. "Aerodynamic Characteristics of NACA 23015 Landing Configuration with 20^o Flap in Simulated Rain." Applied Mechanics and Materials 555 (June 2014): 108–12. http://dx.doi.org/10.4028/www.scientific.net/amm.555.108.

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In our numerical simulation the heavy rain effects have been studied on the aerodynamic performance of 2D cambered NACA 23015 airfoil landing configuration with 20o. We have used preprocessing software gridgen for creation of the landing configuration of the airfoil and then creating mesh around it. Fluent is used to solve the conservation equations. We have used discrete phase modeling (DPM) in Fluent to simulate the rain phenomenon in continuous phase flow by using two phase flow approach. In our study the coupling between the discrete and the continuous phase has been activated. In discrete

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23

Li, Xingxing, and Ke Yang. "Parametric exploration on the airfoil design space by numerical design of experiment methodology and multiple regression model." Proceedings of the Institution of Mechanical Engineers, Part A: Journal of Power and Energy 234, no. 1 (2019): 3–18. http://dx.doi.org/10.1177/0957650919850426.

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Robust airfoil design is crucial to efficient, stable, and safe operation for modern wind turbines. However, even for deterministic wind turbine airfoil design, the problem is complex regarding to aerodynamic, acoustic, and structural requirements of wind turbine blades. Therefore, this study aims to assess the design variable impact, identify significant variables, and obtain the correlation with the airfoil responses, to reduce the cost of the airfoil robust optimization. In this paper, the optimal hypercube design method was applied to an airfoil designed by the National Advisory Committee

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24

Thielicke, William, and Eize J. Stamhuis. "The influence of wing morphology on the three-dimensional flow patterns of a flapping wing at bird scale." Journal of Fluid Mechanics 768 (March 4, 2015): 240–60. http://dx.doi.org/10.1017/jfm.2015.71.

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The effect of airfoil design parameters, such as airfoil thickness and camber, are well understood in steady-state aerodynamics. But this knowledge cannot be readily applied to the flapping flight in insects and birds: flow visualizations and computational analyses of flapping flight have identified that in many cases, a leading-edge vortex (LEV) contributes substantially to the generation of aerodynamic force. In flapping flight, very high angles of attack and partly separated flow are common features. Therefore, it is expected that airfoil design parameters affect flapping wing aerodynamics

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25

Wang, Yuanjing, Binbin Lv, Pengxuan Lei, Wenkui Shi, and Yu Yan. "Study on Flow Mechanism of a Morphing Supercritical Airfoil." Shock and Vibration 2021 (April 19, 2021): 1–11. http://dx.doi.org/10.1155/2021/5588056.

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In order to maintain the best performance in flight, a new concept, morphing aircraft, has been proposed, which can change the real-time aerodynamic characteristics under different flight conditions. The key problem is to figure out the response of strong flow instability caused by structure changes during the morphing. To solve this problem, computational fluid dynamics (CFD) and wind tunnel tests (WTT) were employed. The results show that the deformation of thickness and camber angle of the airfoil will significantly change the distribution of pressure and result in obvious hysteresis loops

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26

Bullen, R. D., and N. L. McKenzie. "Bat wing airfoil and planform structures relating to aerodynamic cleanliness." Australian Journal of Zoology 55, no. 4 (2007): 237. http://dx.doi.org/10.1071/zo07010.

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In this paper we examine 12 species of Western Australian bat for anatomical and morphometric attributes related to wing lift and drag characteristics. We present values for bat wing camber (typically 6.5–9%) and its location, measurements of wing planform and tip shape (typically elliptical but with two different tip designs), dimensions of wing leading-edge flaps (typically 8–10.5% of hand wing chord but with some species having much larger flaps up to 18%) and then discuss several features related to airflow separation control. All species assessed had thin, low-camber airfoil sections, an

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27

El-Salamony, Mostafa, and Mohamed A. Aziz. "Solar Panel Effect on Low-Speed Airfoil Aerodynamic Performance." Unmanned Systems 09, no. 04 (2021): 333–47. http://dx.doi.org/10.1142/s2301385021500175.

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Recently, a great interest in search of alternate means of power for the traditional fuel for aircraft propulsion is raised so as to decrease gas emissions and reduce operating costs. For the small and micro unmanned aerial vehicles or small transportation aircraft, there are many challenges in the direction of constructing an electric or solar powered airplane whose wings may possibly be sheltered with photo voltaic PV solar panels to harvest sun’s energy for propulsion. Greatest remarkably success solar powered aircraft has attracted the attention of researchers other than UAV and small airc

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28

Corona, Jose J., Osama Mesalhy, Louis Chow, Quinn Leland, and John P. Kizito. "The best efficiency point of an axial fan at low-pressure conditions." Advances in Mechanical Engineering 13, no. 3 (2021): 168781402110011. http://dx.doi.org/10.1177/16878140211001188.

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In the current work, the objective is to determine the best efficiency point (BEP) of an axial fan using CFD. Analyzing the performance of the fan based upon the parameters chosen can lead to the optimal design of an axial flow fan for aerospace applications where the ambient pressure varies rapidly. The 2-bladed fan chosen for the study is the Propimax 2L which is considered the base fan used for comparison of all the results of the work. The set of parameters tested were fan rotational speed, ambient pressure conditions, blade count, and the airfoil design. All the performance measures were

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29

Item, Cem C., and Oktay Baysal. "Wing Section Optimization for Supersonic Viscous Flow." Journal of Fluids Engineering 120, no. 1 (1998): 102–8. http://dx.doi.org/10.1115/1.2819632.

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To improve the performance of a highly swept supersonic wing, it is desirable to have an automated design method that also includes a higher fidelity to the flow physics. With this impetus, an aerodynamic optimization methodology incorporating the thin-layer Navier-Stokes equations and sensitivity analysis had previously been developed. Prior to embarking upon the full wing design task, the present investigation concentrated on the identification of effective optimization problem formulations and testing the feasibility of the employed methodology, by defining two-dimensional test cases. Start

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Li, Zhao, Xiaoyan Tong, Jing Sun, et al. "Methods and Criterion for Adaptive Ice Accretion Simulation: Mesh Boundary Merge and Reconstruction." International Journal of Applied Mechanics 12, no. 09 (2020): 2050105. http://dx.doi.org/10.1142/s1758825120501057.

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The strong coupling effect of two-phase flow and ice accompanies the ice accretion process of aircraft and wind turbine in damp and cold environment. A method based on the Eulerian two-phase flow, domain discretization of finite volume method (FVM) and finite element method (FEM), and fluid–solid coupling for numerical simulation of ice accretion is presented in this paper. In addition, the icing process of two-dimensional (2D) ice accretion on airfoils is investigated. It is found that the difference between simulation results and experimental data comes from the phase changes of local collec

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31

Lin, Han-Tang, Yunn-Horng Guu, and Wei-Hsuan Hsu. "Design and Fabrication of a Novel Window-Type Convection Device." Applied Sciences 11, no. 1 (2020): 267. http://dx.doi.org/10.3390/app11010267.

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Global warming, climate change, and ever-increasing energy demand are among the pressing challenges currently facing humanity. Particularly, indoor air conditioning, a major source of energy consumption, requires immediate improvement to prevent energy crises. In this study, various airfoil profiles were applied to create a window-type convection device that entrains air to improve convection between indoor and outdoor airflows and adjust the indoor temperature. How the geometric structure of the convection device affects its air entrainment performance was investigated on the basis of various

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32

Tong, Hui, Jian Fang, Jinyang Guo, Kun Lin, and Ying Wang. "Numerical Simulation of Unsteady Aerodynamic Performance of Novel Adaptive Airfoil for Vertical Axis Wind Turbine." Energies 12, no. 21 (2019): 4106. http://dx.doi.org/10.3390/en12214106.

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The aerodynamic performance of the blade determines the power and load characteristics of a wind turbine. In this paper, numerical research of the active deformation of an airfoil with equal thickness camber line was carried out, which shows the great potential of this active flow control method to improve the flow field. The NACA0012 is taken as the reference airfoil, and the inflow wind speed is 9 m/s, the chord length of the airfoil is 0.4 m, and the Reynolds number is 2.5 × 105. The influence factors, such as deformation amplitude and deformation frequency on the aerodynamic performance, w

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Jacobellis, George, Farhan Gandhi, Thomas T. Rice, and Michael Amitay. "Computational and Experimental Investigation of Camber-Morphing Airfoils for Reverse Flow Drag Reduction on High-Speed Rotorcraft." Journal of the American Helicopter Society 65, no. 1 (2020): 1–14. http://dx.doi.org/10.4050/jahs.65.012001.

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Through computational fluid dynamics simulations and wind tunnel tests, this study examines a NACA 63-218 airfoil in reverse flow at Rec=375,000 and demonstrates reduction in reverse flow drag through the introduction of reflex camber. Of the three contributors to drag—ram pressure on the upper surface near the trailing edge, suction on the lower surface near the trailing edge, and bluff body separation at the rounded nose—reflex camber (where the camber line near the trailing edge of the airfoil is deflected upward) influences the first two, reducing exposure to ram drag on the upper surface

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Brigido-González, J. David, Steve G. Burrow, and Benjamin KS Woods. "Switchable stiffness morphing aerostructures based on granular jamming." Journal of Intelligent Material Systems and Structures 30, no. 17 (2019): 2581–94. http://dx.doi.org/10.1177/1045389x19862372.

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One of the persistent challenges facing the development of morphing aerostructures is the need to have material and structural solutions which provide a compromise between the competing design drivers of low actuation energy and high stiffness under external loads. This work proposes a solution to this challenge in the form of a novel switchable stiffness structural concept based on the principle of granular jamming. In this article, the concept of using granular jamming for controlling stiffness is first introduced. Four-point bending tests are used to obtain the flexural rigidity and bending

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35

Hayami, Itaru. "Living and fossil scallop shells as airfoils: an experimental study." Paleobiology 17, no. 1 (1991): 1–18. http://dx.doi.org/10.1017/s0094837300010319.

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Selected shell specimens of extant and fossil streamlined pectinids, which have or presumably had level-swimming ability, were examined experimentally to elucidate their hydrodynamic properties, in particular, airfoil efficiency estimated by lift-drag ratio. Using a stationary water tank for nautical engineering, lift and drag forces were measured at various attack angles. Of the examined species, Amusium japonicum, which is characterized by an unusually shiny surface, upward-cambered commissure and sharpened trailing edge, is the most efficient level swimmer and has the lowest drag coefficien

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Forouzi Feshalami, Behzad, MH Djavareshkian, AH Zaree, Masoud Yousefi, and AA Mehraban. "The role of wing bending deflection in the aerodynamics of flapping micro aerial vehicles in hovering flight." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 10 (2018): 3749–61. http://dx.doi.org/10.1177/0954410018806081.

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Scientists have been improving the aerodynamic performance of flapping micro aerial vehicles by drawing inspiration from birds and insect flight. In this research study, first, the flapping mechanism of the black-headed gull is designed and then it is constructed in order to investigate the effects of wing bending deflection on the aerodynamic performance. Thrust generation, power consumption and power loading are considered as performance parameters. Three wings representing different underlying structures, namely flexible membrane, rigid membrane and airfoil, are fabricated with the same pla

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Tao, Yuan, Xianjun Yu, and Baojie Liu. "A New Method for Rapid Optimization Design of a Subsonic Tandem Blade." Applied Sciences 10, no. 24 (2020): 8802. http://dx.doi.org/10.3390/app10248802.

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Tandem blade technology has been developed for years due to its capacity to bear higher aerodynamics than conventional configurations. Even so, there is still the tough problem of how to design tandem blades effectively and further improve blade performance. This paper tries to further understand the flow characteristics of tandem blades in order to present a new method of designing them under subsonic inflow conditions. Firstly, efforts were made to reveal the aerodynamic interaction between the forward blade (FB) and the aft blade (AB). Secondly, considering this aerodynamic interaction, the

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Bornengo, D., F. Scarpa, and C. Remillat. "Evaluation of hexagonal chiral structure for morphing airfoil concept." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 219, no. 3 (2005): 185–92. http://dx.doi.org/10.1243/095441005x30216.

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In this paper a concept of hexagonal chiral honeycomb is proposed as a truss-like internal structure for adaptive wing box configurations. In contrast with classical centresym-metric cellular structures like rectangular or hexagonal grids, the proposed honeycomb did not present inversion symmetry, and featured an in-plane negative Poisson's ratio behaviour. The cellular structure considered exhibited this Poisson's ratio behaviour under a large range of strain. A set of numerical (finite element, FE) simulations have been carried out in order to correct the initial theoretical predictions to t

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Gürses, Ercan, İlhan Ozan Tunçöz, Yosheph Yang, et al. "Structural and aerodynamic analyses of a hybrid trailing edge control surface of a fully morphing wing." Journal of Intelligent Material Systems and Structures 28, no. 8 (2016): 979–91. http://dx.doi.org/10.1177/1045389x16641200.

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In this article, the design and analysis of a hybrid trailing edge control surface of an unmanned aerial vehicle are presented. The structural design was performed to increase and decrease the camber of the control surface to match selected airfoil profiles. The design was first analyzed with the help of finite element method to assess the morphing capability. The morphed control surface was then analyzed aerodynamically and comparisons with the original target profiles were made. According to the aerodynamic analyses, it was concluded that the control surface can successfully morph into targe

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Speziale, C. G., F. Sisto, and S. Jonnavithula. "Vortex Simulation of Propagating Stall in a Linear Cascade of Airfoils." Journal of Fluids Engineering 108, no. 3 (1986): 304–12. http://dx.doi.org/10.1115/1.3242578.

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A numerical simulation of propagating stall in a linear cascade of airfoils at high Reynolds numbers is conducted using a vortex method which was first developed by Spalart [7] for this problem. In this approach, the vorticity is discretized into a large collection of vortex blobs whose motion is tracked in time by the use of a well-known vortex tracing algorithm based on the Euler equation. The near-wall effects of viscosity are accounted for by the creation of discrete vortex sheets at the boundaries of the airfoils consistent with the no-slip condition. These boundary vortices are then rele

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Guo, Xiangying, Pan Jiang, and Dongxing Cao. "Influence of Piezoelectric Performance on Nonlinear Dynamic Characteristics of MFC Shells." Complexity 2019 (October 9, 2019): 1–15. http://dx.doi.org/10.1155/2019/1970248.

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Based on the structures of unmanned aerial vehicle (UAV) wings, nonlinear dynamic analysis of macrofiber composite (MFC) laminated shells is presented in this paper. The effects of piezoelectric properties and aerodynamic forces on the dynamic stability of the MFC laminated shell are studied. Firstly, under the flow condition of ideal incompressible fluid, the thin airfoil theory is employed to calculate the effects of the mean camber line to obtain the circulation distribution of the wings in subsonic air flow. The steady aerodynamic lift on UAV wings is derived by using the Kutta–Joukowski l

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Smith, L. H. "M. J. Hartmann Memorial Session Paper: NASA/GE Fan and Compressor Research Accomplishments." Journal of Turbomachinery 116, no. 4 (1994): 555–69. http://dx.doi.org/10.1115/1.2929445.

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Fan and compressor research projects carried out at GE Aircraft Engines under NASA sponsorship are described in this paper. Four 1400-fps-tip-speed rotors designed with different airfoil shapes were found to have comparable stall lines but different efficiency trends. A stator placed behind one of these affected its performance somewhat. Adjustments of variable camber inlet guide vanes placed ahead of a 1500fps stage were found to affect its pumping capability without much affecting its stall line. For the Quiet Engine Program (QEP), two 1160-fps fans and one 1550-fps fan were tested. Developm

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EVERS, I., and N. PEAKE. "Noise generation by high-frequency gusts interacting with an airfoil in transonic flow." Journal of Fluid Mechanics 411 (May 25, 2000): 91–130. http://dx.doi.org/10.1017/s0022112099008095.

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The method of matched asymptotic expansions is used to describe the sound generated by the interaction between a short-wavelength gust (reduced frequency k, with k [Gt ] 1) and an airfoil with small but non-zero thickness, camber and angle of attack (which are all assumed to be of typical size O(δ), with δ [Lt ] 1) in transonic flow. The mean-flow Mach number is taken to differ from unity by O(δ2/3), so that the steady flow past the airfoil is determined using the transonic small-disturbance equation. The unsteady analysis is based on a linearization of the Euler equations about the mean flow.

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EVERS, I., and N. PEAKE. "On sound generation by the interaction between turbulence and a cascade of airfoils with non-uniform mean flow." Journal of Fluid Mechanics 463 (July 25, 2002): 25–52. http://dx.doi.org/10.1017/s0022112002008698.

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The sound generated by the interaction between a turbulent rotor wake and a stator is modelled by considering the gust response of a cascade of blades in non-uniform, subsonic mean flow. Previous work by Hanson & Horan (1998) that considers a cascade of flat plates at zero incidence is extended to take into account blade geometry and angle of attack. Our approach is based on the work of Peake & Kerschen (1997), who calculate the forward radiation due to the interaction between a single vortical gust and a cascade of flat plates at non-zero angle of attack. The extensions completed in t

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PEAKE, N., and E. J. KERSCHEN. "Influence of mean loading on noise generated by the interaction of gusts with a flat-plate cascade: upstream radiation." Journal of Fluid Mechanics 347 (September 25, 1997): 315–46. http://dx.doi.org/10.1017/s0022112097006502.

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The sound generated by the interaction between convected vortical and entropic disturbances and a blade row is a significant component of the total noise emitted by a modern aeroengine, and the blade geometry has an important effect on this process. As a first step in the development of a general prediction scheme, we model in this paper just the action of the blade mean loading by treating the blades as flat plates aligned at a non-zero incidence angle, δ, to the oncoming stream, and consider harmonic components of the incident field with reduced frequency k. We then use asymptotic analysis i

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Liu, Chunbao, Konghua Yang, Jing Li, Zhixuan Xu, and Tongjian Wang. "Performance improvement and flow field investigation in hydraulic torque converter based on a new design of segmented blades." Proceedings of the Institution of Mechanical Engineers, Part D: Journal of Automobile Engineering 234, no. 8 (2020): 2162–75. http://dx.doi.org/10.1177/0954407019899507.

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Hydraulic torque converter is of lower efficiency in the powertrain, particularly at low speed ratio, which is crucial for vehicles due to its ability of torque multiplication. Therefore, torque converters should be taken into account with both higher start-up acceleration and transmission efficiency. Inspired by the fact that the multi-airfoils of the aircraft can improve the lift, a new design of segmented turbine blade in torque converter is presented to improve the transmission efficiency and start-up acceleration. To ensure reproducibility and popularization, the camber line and shape of

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Chen, Zhaolin, Tianhang Xiao, Yan Wang, and Ning Qin. "Laminar separation bubble dynamics and its effects on thin airfoil performance during pitching-up motion." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, March 11, 2021, 095441002199952. http://dx.doi.org/10.1177/0954410021999529.

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This article reports an investigation into dynamic characteristics of the laminar separation bubbles (LSBs) associated with aerodynamic loads unsteadiness of a cambered thin airfoil in pitching-up motions at low Reynolds number flows. Unsteady Reynolds-averaged Navier–Stokes (URANS) simulations were conducted for a 4%c cambered thin airfoil at Reynolds number of 30,000 and 60,000. The airfoil pitches up from 0° to 25°angles of attack at dimensionless pitch rate [Formula: see text] of 0.0398 and 0.0199. The [Formula: see text] SST [Formula: see text] turbulence transition model was used to acco

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Ligrani, Phil, and Jae Sik Jin. "Second Law Analysis of Aerodynamic Losses: Results for a Cambered Vane With and Without Film Cooling." Journal of Turbomachinery 135, no. 4 (2013). http://dx.doi.org/10.1115/1.4007588.

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Results of second law analysis of experimentally-measured aerodynamic losses are presented for a cambered vane with and without film cooling, including comparisons with similar results from a symmetric airfoil. Included are distributions of local entropy creation, as well as mass-averaged magnitudes of global exergy destruction. The axial chord length of the cambered vane is 4.85 cm, the true chord length is 7.27 cm, and the effective pitch is 6.35 cm. Data are presented for three airfoil Mex distributions (including one wherein the flow is transonic), magnitudes of inlet turbulence intensity

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Rusak, Zvi, and Wallace J. Morris. "Stall Onset on Airfoils at Moderately High Reynolds Number Flows." Journal of Fluids Engineering 133, no. 11 (2011). http://dx.doi.org/10.1115/1.4005101.

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The inception of leading-edge stall on two-dimensional smooth thin airfoils at moderately high Reynolds number flows [in the range O(104) to O(106)] is investigated by an asymptotic approach and numerical simulations. The asymptotic theory is based on the work of Rusak (1994) and demonstrates that a subsonic flow about a thin airfoil can be described in terms of an outer region, around most of the airfoil chord, and an inner region, around the nose, that asymptotically match each other. The flow in the outer region is dominated by the classical thin airfoil theory. Scaled (magnified) coordinat

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Bianchini, Alessandro, Francesco Balduzzi, John M. Rainbird, et al. "An Experimental and Numerical Assessment of Airfoil Polars for Use in Darrieus Wind Turbines—Part I: Flow Curvature Effects." Journal of Engineering for Gas Turbines and Power 138, no. 3 (2015). http://dx.doi.org/10.1115/1.4031269.

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A better comprehension of the aerodynamic behavior of rotating airfoils in Darrieus vertical-axis wind turbines (VAWTs) is crucial both for the further development of these machines and for improvement of conventional design tools based on zero- or one-dimensional models (e.g., blade element momentum (BEM) models). When smaller rotors are designed with high chord-to-radius (c/R) ratios so as not to limit the blade Reynolds number, the performance of turbine blades has been suggested to be heavily impacted by a virtual camber effect imparted on the blades by the curvilinear flow they experience

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