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Journal articles on the topic 'Attack angle'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 July 2025

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1

Teja, J. Navya, Aslesha Bodavula, and Govardhan Dussa. "Aerodynamic Performance Assessment of an Airfoil at Reynolds Number 10000: A Computational Approach." International Journal of Membrane Science and Technology 10, no. 4 (2023): 1400–1413. http://dx.doi.org/10.15379/ijmst.v10i4.2256.

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Effects of a low Reynolds number flow on an airfoil with cavities of a specified shape are analyzed computationally to assess the aerodynamic performance by observing the coefficients of lift and drag with increasing angles of attacks. The Reynolds number considered for the simulation is 1×104 operating at atmospheric conditions at sea level. Indentations with a definite shape (right-angled triangle) are utilized to find the vortex effects of air in the cavity on the shear layer separation on airfoil surface to retain the flow even at higher angles of attack. The simulation is run in ANSYS Flu

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2

Haryanto, Ismoyo, Khoiri Rozi, Berkah Fajar TK, and Alwahidil Zuhri. "Analysis of Aerodynamics Load of a Flapping Wing by Vortex Lattice Method." International Research Journal of Innovations in Engineering and Technology 08, no. 09 (2024): 297–301. http://dx.doi.org/10.47001/irjiet/2024.809036.

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The aim of this study is to investigate the effect of changing the angle of attack and flapping angle on the aerodynamic characteristics of an unsymmetrical wing with the NACA 2412 profile. This work uses the Vortex Lattice Method. The results of this study show that increasing the flapping angle causes the pitching moment to decrease while induced drag and moment coefficient increase, meanwhile, the lift coefficient increases at positive angles of attack and then decreases at negative angles of attack. The pitching moment decreases with increasing angle of attack at positive flap angles, but

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3

Jiang, Hai Bo, Yan Ru Li, and Zhong Qing Cheng. "Relations of Lift and Drag Coefficients of Flow around Flat Plate." Applied Mechanics and Materials 518 (February 2014): 161–64. http://dx.doi.org/10.4028/www.scientific.net/amm.518.161.

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In this paper, when Reynolds number is within the range of 10000 to 1000000, the horizontal component of the total pressure of flow around flat plate at high angle of attack was regarded as lift of high angle of attack, and the vertical component was regarded as drag of high angle of attack. The horizontal component of total pressure at small angle of attack was regarded as shape drag, and the total drag coefficient at small angle of attack was considered to the sum of the shape drag and frictional drag at zero angle of attack. For the two states of large and small angle of attack, the applica

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4

Brice, Jennifer. "Angle of Attack." River Teeth: A Journal of Nonfiction Narrative 6, no. 1 (2004): 17–40. http://dx.doi.org/10.1353/rvt.2005.0003.

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5

Yeston, J. "Angle of Attack." Science 337, no. 6096 (2012): 779. http://dx.doi.org/10.1126/science.337.6096.779-b.

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6

Gatti-Bono, Caroline, and N. C. Perkins. "Effect of Loop Shape on the Drag-Induced Lift of Fly Line." Journal of Applied Mechanics 71, no. 5 (2004): 745–47. http://dx.doi.org/10.1115/1.1778414.

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This note explains why casting a loop with a positive angle of attack is advantageous in distance fly casting. Several loop shapes, one with a positive angle of attack, one with a negative angle of attack, and two symmetrical loops with zero angle of attack are studied. For each loop, we compute the vertical drag component, i.e., the “lift.” It is found that a loop with a positive angle of attack generates lift about four times larger than a symmetrical loop. Thus, loops with positive angles of attack stay “aerialized longer” which is consistent with observations made by (competition) distance

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7

Tang, Hui, Yulong Lei, Xingzhong Li, and Yao Fu. "Numerical investigation of the aerodynamic characteristics and attitude stability of a bio-inspired corrugated airfoil for MAV or UAV applications." Energies 12, no. 20 (2019): 4021. http://dx.doi.org/10.3390/en12204021.

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In this study, two-dimensional (2D) and three-dimensional (3D) numerical calculations were conducted to investigate the aerodynamic characteristics, especially the unsteady aerodynamic characteristics and attitude stability of a bio-inspired corrugated airfoil compared with a smooth-surfaced airfoil (NACA2408 airfoil) at the chord Reynolds number of 4000 to explore the potential applications of non-traditional, corrugated dragonfly airfoils for micro air vehicles (MAVs) or micro-sized unmanned aerial vehicles (UAVs) designs. Two problem settings were applied to our numerical calculations. Firs

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8

Sun, Yong, and Xing Sheng Li. "Determination of Attack Angle and Tilt Angle of a Cutting Pick." Advanced Materials Research 705 (June 2013): 415–18. http://dx.doi.org/10.4028/www.scientific.net/amr.705.415.

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Mechanical excavators play an important role in mining and construction. An excavation machine cuts rocks using its cutterhead which is normally composed of a large number of cutting picks. These picks are installed on a drum with certain attack angles, tilt angles and skew angles. These angles, especially attack and tilt angles, will affect the forces acting on individual picks and the cutterhead. To ensure the reliability and productivity of the excavation machine, these angles have to be kept in their optimal values. However, in manufacturing, these three types of angles cannot be set simul

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9

Xu, Yihang, Shaosong Chen, and Hang Zhou. "Analysis of the Magnus Moment Aerodynamic Characteristics of Rotating Missiles at High Altitudes." International Journal of Aerospace Engineering 2021 (April 12, 2021): 1–13. http://dx.doi.org/10.1155/2021/6623510.

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The Magnus moment characteristics of rotating missiles with Mach numbers of 1.3 and 1.5 at different altitudes and angles of attack were numerically simulated based on the transition SST model. It was found that the Magnus moment direction of the missiles changed with the increase of the angle of attack. At a low altitude, with the increase of the angle of attack, the Magnus moment direction changed from positive to negative; however, at high altitudes, with the increase of the angle of attack, the Magnus moment direction changed from positive to negative and then again to positive. The Magnus

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10

Zhang, Li, Xinru Mao, and Lin Ding. "Influence of attack angle on vortex-induced vibration and energy harvesting of two cylinders in side-by-side arrangement." Advances in Mechanical Engineering 11, no. 1 (2019): 168781401882259. http://dx.doi.org/10.1177/1687814018822598.

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The vortex-induced vibration and energy harvesting of two cylinders in side-by-side arrangement with different attack angles are numerically investigated using two-dimensional unsteady Reynolds-Averaged Navier–Stokes simulations. The Reynolds number ranges from 1000 to 10,000, and the attack angle of free flow is varied from 0° to 90°. Results indicate that the vortex-induced vibration responses with attack angle range of 0°≤ α ≤ 30° are stronger than other attack angle cases. The parallel vortex streets are clearly observed with synchronized vortex shedding. Relatively large attack angle lead

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11

Gollomp, B. "The angle of attack." IEEE Instrumentation & Measurement Magazine 4, no. 1 (2001): 57–58. http://dx.doi.org/10.1109/5289.911179.

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12

Li, Yang, Hao Zhou, and Wanchun Chen. "Three-Dimensional Impact Time and Angle Control Guidance Based on MPSP." International Journal of Aerospace Engineering 2019 (February 24, 2019): 1–16. http://dx.doi.org/10.1155/2019/5631723.

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A new nonlinear guidance law for air-to-ground missile cooperation attacks is proposed in this paper. This guidance law enables missiles with different initial conditions to attack targets simultaneously, and it can also precisely satisfy the terminal impact angle conditions in both flight-path angle and heading angle. The guidance law is devised using the model predictive static programming (MPSP) method, and the control saturation constraint is incorporated in the MPSP algorithm. The first-order-lag acceleration of the missile is taken as the state variable to realize the convergence of the

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13

Hu, Haode, and Dongli Ma. "Airfoil Aerodynamics in Proximity to Wavy Ground for a Wide Range of Angles of Attack." Applied Sciences 10, no. 19 (2020): 6773. http://dx.doi.org/10.3390/app10196773.

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Wing-in-ground craft often encounter waves when flying over the sea surface, and the ground effect is more complicated than that of flat ground. Therefore, the aerodynamic characteristics of the NACA 4412 airfoil in proximity to wavy ground for a wide range of angles of attack is studied by solving the Reynolds Averaged Navier–Stokes equations. The validation of the numerical method is carried out by comparing it with the experimental data. The results show that the aerodynamic coefficients will fluctuate periodically when the airfoil moves over wavy ground at a small ride height. Except for t

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14

Popowski, Stanisław, and Witold Dąbrowski. "MEASUREMENT AND ESTIMATION OF THE ANGLE OF ATTACK AND THE ANGLE OF SIDESLIP." Aviation 19, no. 1 (2015): 19–24. http://dx.doi.org/10.3846/16487788.2015.1015293.

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The paper presents issues concerning the estimation of the angle of attack and the angle of sideslip on a flying object board. Angle of attack and sideslip estimation methods which are based on measurements of linear velocity components of an object with the Earth’s coordinates and on attitude angles of the object are presented. Both of these measurements originate from the inertial navigation system, and velocity measurement is obtained from the satellite navigation system. The idea of applying inertial and satellite navigation for the estimation of attack and sideslip angles is presented. Pr

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15

Zhao, Yuanyuan, Qiang Fu, Rongsheng Zhu, Guoyu Zhang, Chuan Wang, and Xiuli Wang. "Transient Process and Micro-mechanism of Hydrofoil Cavitation Collapse." Processes 8, no. 11 (2020): 1387. http://dx.doi.org/10.3390/pr8111387.

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Cavitation will cause abnormal flow, causing a series of problems such as vibration, noise, and erosion of solid surfaces. In severe cases, it may even destroy the entire system. Cavitation is a key problem to be solved for hydraulic machinery and underwater robots, and the attack angle is one of the most important factors affecting the cavitation. In order to systematically study the impact of the attack angle on the hydrofoil cavitation, the hydrofoils of NACA 4412 with different attack angles were selected to study the collapse process and hydraulic characteristics such as pressure, velocit

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16

Yasuda, Akane, Tomoki Taniguchi, and Toru Katayama. "Numerical Investigation of Aerodynamic Interactions between Rigid Sails Attached to Ship." Journal of Marine Science and Engineering 12, no. 8 (2024): 1425. http://dx.doi.org/10.3390/jmse12081425.

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As part of the strategy to achieve net-zero Greenhouse Gas (GHG) emissions in international maritime shipping, there is ongoing exploration into the use of wind propulsion systems as auxiliary ship propulsion devices. When considering a rigid sail as the wind propulsion system, evaluating the performance of a single sail is relatively simple. However, assessing the performance of multiple sails is more challenging due to the interference between the sails and between the sails and the hull. In this study, the thrust characteristics of two rigid sails attached to a ship are investigated by usin

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17

Molatudi, Errol, Thokozani Justin Kunene, and Lagouge Kwanda Tartibu. "A Ffowcs Williams-Hawkings numerical aeroacoustic study of varied and fixed-pitch blades of an H-Rotor vertical axis wind turbine." MATEC Web of Conferences 347 (2021): 00013. http://dx.doi.org/10.1051/matecconf/202134700013.

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The effects of sound pressure level at two observation positions of a fixed and varied blade pitch angle at Low-Mach unsteady incompressible Reynolds-Average Navier-Stokes flow approach, on an H-rotor Vertical Axis Wind Turbine. The objective of the study is to compare the noise dissipation and output power/energy of the airfoil blades design of the vertical axis wind turbine in residential zones. The Ffowcs Williams-Hawkings (FHWH) techniques were applied to validate the output noise and vortex shedding of the different angles of attacks (AoA). The study postulated that the time history of th

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18

Guo, Da Fei, Jian Xiang Xu, and Ju Yuan. "Numerical Simulation on the Dynamic Stall of the Horizontal-Axis Wind Turbine." Applied Mechanics and Materials 448-453 (October 2013): 1888–91. http://dx.doi.org/10.4028/www.scientific.net/amm.448-453.1888.

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With the variation of the unsteady incoming flow and impeller rotation, when attack angles of the incoming flow is bigger than the critical angle of attack, there are unsteady separation and dynamic stall on the pressure surface of the impeller. Dynamic stalls are of common occurrence during wind turbines operation. And the aerodynamic characteristics and efficiency of wind turbine are largely affected by the dynamic stall.Therefore,the study of dynamic stall has a great significance over the optimization design of the wind turbine. The paper performs numerical simulation in the dynamic stalls

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19

Long, Wei, Zai Shuai Ling, and Zhen Dang. "The Analysis about External Compressible Flow around an Aircraft Wing." Advanced Materials Research 1044-1045 (October 2014): 654–58. http://dx.doi.org/10.4028/www.scientific.net/amr.1044-1045.654.

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The Steady flow simulation to selected the delta wing model for different angles of attack in the Maher number.The law of flow field changes with the angle of attack is gotten.Through the FLUENT simulation,The variation tendency of coefficient of lift and drag in the different angle of attack is gotten.Further reveals the change rule of Maher number, pressure, velocity and other parameters in the different angle of attack.With increasing angle of attack, Maher number distribution is sparse of the same position increases and the greater numerical.the distribution of velocity vector is sparse of

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20

Liu, Chuan-Zhen, and Peng Bai. "Nonlinear lift increase at high angles of attack for double swept waverider." International Journal of Modern Physics B 34, no. 14n16 (2020): 2040124. http://dx.doi.org/10.1142/s0217979220401244.

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The nonlinear increase of the lift of the double swept waverider at high angles of attack is of vital interest. The aerodynamic performance of the double swept waverider is calculated and compared with that of single swept waveriders. Results suggest that the lift nonlinearity of the double swept waverider is stronger than that of equal-planform-area single swept one, and the nonlinearity increases as Mach number increases. Some scholars have proposed the “vortex lift” to explain the nonlinear lift increase, but it is questionable as the main lift of the waverider comes from the lower surface

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21

Krammer, Oliver, László Jakab, Balazs Illes, David Bušek, and Ivana Beshajová Pelikánová. "Investigating the attack angle of squeegees with different geometries." Soldering & Surface Mount Technology 30, no. 2 (2018): 112–17. http://dx.doi.org/10.1108/ssmt-09-2017-0023.

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Purpose The attack angle of stencil printing squeegees with different geometries was analysed using finite element modelling. Design/methodology/approach A finite element model (FEM) was developed to determine the attack angle during the stencil printing. The material properties of the squeegee were included in the model according to the parameters of steel AISI 4340, and the model was validated by experimental measurements. Two geometric parameters were investigated; two different unloaded angles (45° and 60°) and four overhang sizes of the squeegee (6, 15, 20 and 25 mm). Findings It was foun

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22

Mitryukova, E. A., O. V. Mishchenkova, and A. A. Chernova. "Some aspects in the numerical simulation of the aerodynamics of a NACA 0012 airfoil." Diagnostics, Resource and Mechanics of materials and structures, no. 3 (June 2024): 29–40. http://dx.doi.org/10.17804/2410-9908.2024.3.029-040.

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The paper discusses the numerical simulation of the aerodynamics of an airfoil at different angles of attack. Two approaches to determining the angle of attack are considered: by changing the position of the velocity vector of the oncoming flow and by changing the relative position of the flat airfoil. The value of the angle of attack varies in the range from −5 to +10°. Numerical simulation is performed with the openFoam package for solving continuum mechanics problems in the stationary setting based on finite volumes using the rhoSimpleFoam solver. The study results in the values of flow vel

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23

N, Prajwal, and Kushal Chatterjee. "Effects on Aircraft Performance Due to Geometrical Twist of Wing." Acceleron Aerospace Journal 2, no. 3 (2024): 184–94. http://dx.doi.org/10.61359/11.2106-2410.

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This paper provides an overview of the effects of Geometric Twist on Aircraft performance by introducing a washout condition in an aircraft wing. This condition results in an effective Angle of Attack at the wingtip that is lower than the Angle of Attack at the wing root. Using CFD analysis, the variation of aircraft performance factors such as lift, drag coefficients, and aerodynamic efficiency is calculated for different Twist angles. A plot of lift and drag coefficients at varying Angle of Attack angles has been generated based on these analyses. These results illustrate the advantages of w

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24

FIGAT, Marcin, and Zdobysław GORAJ. "ANALYSIS OF STABILITY DERIVATIVES IMPORTANT TO RECOVERY FROM SPIN." Aviation 20, no. 2 (2016): 48–52. http://dx.doi.org/10.3846/16487788.2016.1195060.

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This paper describes the numerical analysis of light aircraft stability derivatives in a wide range of angles of attack, important for recovery from spin. Stability derivatives versus angle of attack and sideslip were calculated using a CFD software, based on Euler equation combined with boundary layer equations. The analysis was performed up to the 40 deg of angle of attack and up to 25 deg of sideslip.

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25

Jung, Jung-Mo, Yoshiki Matsushita, and Seonghun Kim. "Study on Reducing Towing Drag by Varying the Shape and Arrangement of Floats and Gears." Applied Sciences 12, no. 15 (2022): 7606. http://dx.doi.org/10.3390/app12157606.

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Many studies have been conducted with the aim of reducing fuel consumption by the fishing industry. We examined whether drag can be reduced by changing the arrangement of gears without requiring the development of new parts for the conventional float and ground gear. Ten differently shaped floats and ground gears were measured in a water flume tank. The float and ground gear were fixed to a steel rod to measure fluid drag according to attack angle, using a multi-component load cell. To estimate the frictional drag of ground gear on the seabed, five types of large ground gear were towed on flat

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26

Lacagnina, Giovanni, Paruchuri Chaitanya, Jung-Hoon Kim, et al. "Leading edge serrations for the reduction of aerofoil self-noise at low angle of attack, pre-stall and post-stall conditions." International Journal of Aeroacoustics 20, no. 1-2 (2021): 130–56. http://dx.doi.org/10.1177/1475472x20978379.

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This paper addresses the usefulness of leading edge serrations for reducing aerofoil self-noise over a wide range of angles of attack. Different serration geometries are studied over a range of Reynolds number [Formula: see text]. Design guidelines are proposed that permit noise reductions over most angles of attack. It is shown that serration geometries reduces the noise but adversely effect the aerodynamic performance suggesting that a trade-off should be sought between these two considerations. The self-noise performance of leading edge serrations has been shown to fall into three angle of

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27

Baigang, Mi, and Yu Jingyi. "An Improved Nonlinear Aerodynamic Derivative Model of Aircraft at High Angles of Attack." International Journal of Aerospace Engineering 2021 (September 8, 2021): 1–12. http://dx.doi.org/10.1155/2021/5815167.

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The classical aerodynamic derivative model is widely used in flight dynamics, but its application is extremely limited in cases with complicated nonlinear flows, especially at high angles of attack. A modified nonlinear aerodynamic derivative model for predicting unsteady aerodynamic forces and moments at a high angle of attack is developed in this study. We first extend the higher-order terms to describe the nonlinear characteristics and then introduce three more influence parameters, the initial angle of attack, the reduced frequency, and the oscillation amplitude, to correct the constant ae

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28

Arnab, Manish Bhadra, and Mohammad Ilias Inam. "Comparison of Aerodynamic Performance of NACA 23012 and NACA 4412 Airfoil: A Numerical Approach." SciEn Conference Series: Engineering 1 (May 7, 2025): 113–18. https://doi.org/10.38032/scse.2025.1.21.

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Two of the most widely used airfoils worldwide are NACA 23012 and NACA 4412. The purpose of this study is to investigate and compare the aerodynamic characteristics of these two airfoils for a constant Reynolds number of 5×106. These simulations were conducted in 2D using Spalart-Allmaras as turbulence model by ANSYS Fluent. Numerical results demonstrate that lift coefficient increases with angle of attack up to certain values, after that it decreases due to flow separation. The drag coefficient also increases with angle of attack for both airfoils. However, the rate of increment is much highe

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29

Fazylova, Alina, Michail Malamatoudis, and Panagiotis Kogias. "Optimization of the blade profile of a vertical axis wind turbine based on aerodynamic analysis." E3S Web of Conferences 404 (2023): 02002. http://dx.doi.org/10.1051/e3sconf/202340402002.

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This paper explores the influence of the angle of attack on the aerodynamic characteristics of the blade profile. The paper presents calculations, modeling and graphical representation of the blade shape during rotation around the axis. Using the given parameters, such as the length of the blade, the radius of the upper and lower boundaries, as well as the angle of inclination of the blade, the calculation of the coordinates of the points of the blade profile for various angles of rotation is given. The cross-sectional area, volume and mass of the blade were also calculated. Appropriate calcul

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30

Zhao, Jie, Xiong Wei Liu, Lin Wang, and Xin Zi Tang. "Design Attack Angle Analysis for Fixed-Pitch Variable-Speed Wind Turbine." Advanced Materials Research 512-515 (May 2012): 608–12. http://dx.doi.org/10.4028/www.scientific.net/amr.512-515.608.

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The purpose of this paper is to find the optimum design attack angle for fixed-pitch variable-speed wind turbine blade design, given the base-line wind turbine and the blade airfoil. Aerodynamic characteristics, i.e. lift and drag coefficients and lift to drag ratio, of the wind turbine, are analyzed. Two design attack angles along with the base-line attack angle (with maximum lift to drag ratio) are selected for the wind turbine blade design exercise. Blade design outcomes are analyzed and compared along with load performance and power performance. This paper is possibly the first attempt to

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31

Kang, Xiaozhi, Lin Du, Qinchuan Shi, and Xiaoyu Wang. "Fluid-thermally-solid coupling analysis of aircraft leading edge." Journal of Physics: Conference Series 2882, no. 1 (2024): 012098. http://dx.doi.org/10.1088/1742-6596/2882/1/012098.

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Abstract Aircraft are affected by aerodynamic loads during operation. To analyze the impact of the leading edge structure of aircraft under different flight angles of attack, this paper uses the fluid-heat-solid coupling calculation method. It combines CFD with the thermal-structure field solver and uses simulation software, with a flight altitude of 15 km, flight speed of 6 Ma, and flight Angle of attack of 0 ~ 20°. Considering the change of material parameters with temperature, the coupling of multiple physical fields in aircraft is simulated and analyzed. The simulation results show that th

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32

Dos Santos, Guilherme P., Adriano Kossoski, Jose M. Balthazar, and Angelo Marcelo Tusset. "SDRE and LQR Controls Comparison Applied in High-Performance Aircraft in a Longitudinal Flight." International Journal of Robotics and Control Systems 1, no. 2 (2021): 131–44. http://dx.doi.org/10.31763/ijrcs.v1i2.329.

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This paper presents the design of the LQR (Linear Quadratic Regulator) and SDRE (State-Dependent Riccati Equation) controllers for the flight control of the F-8 Crusader aircraft considering the nonlinear model of longitudinal movement of the aircraft. Numerical results and analysis demonstrate that the designed controllers can lead to significant improvements in the aircraft's performance, ensuring stability in a large range of attack angle situations. When applied in flight conditions with an angle of attack above the stall situation and influenced by the gust model, it was demonstrated that

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33

Cao, Yu Ji, Shi Ying Zhang, and Peng Gao. "Investigation of Attack Angle Character for Hypersonic Inlet." Advanced Materials Research 468-471 (February 2012): 1978–81. http://dx.doi.org/10.4028/www.scientific.net/amr.468-471.1978.

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The comparison analysis of performance with design point has been done in view of two different inlets, which were built by uniform shock intensity and shock angle method respectively. Base on this, the attack angle performance was emphatic developed on off-design point. The numerical calculation and analysis was conducted in eight different attack angle for air inlet conditions on two kinds of inlet respectively. The result indicated that, the inlet with uniform shock intensity method has 5% much more flow coefficient than inlet with uniform shock angle, in the condition of design point. In t

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34

Тлеулинов, М. К. "Бифуркация Пуанкаре-Андронова-Хопфа в колебаниях прощелкивания составных несущих и управляющих поверхностей летательных аппаратов". Письма в журнал технической физики 45, № 15 (2019): 47. http://dx.doi.org/10.21883/pjtf.2019.15.48088.17656.

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Oscillations of a catastrophic change in shape (oscillations of clicking) compound lifting and control surfaces interconnected in a statically indefinable manner are considered. The influence of the angle of attack on the nature of oscillations is investigated. The phase portraits of the twisting angle of the control surface at different angles of attack are given.

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35

Dincă, Liviu, Jenica-Ileana Corcău, and Dionis Cumpan. "Two Numerical Studies for Longitudinal Movement of a Canard UAV with Vectored Thrust." Annals of the University of Craiova, Electrical Engineering Series 45, no. 1 (2021): 90–97. http://dx.doi.org/10.52846/aucee.2021.1.13.

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This work presents a study concerning the possibilities to improve the longitudinal dynamic of a canard UAV using vectored thrust. It is followed to harness the advantages of canard configuration of UAV and to obtain further a better longitudinal dynamic, able to fulfil more complex missions than canard UAV without vectored thrust. There are tested two methods. The first uses the UAV polars obtained in XFLR 5 and extended, using literature experience, a little bit over the stall angle. By this method is determined the necessary gain between the elevator steering angle and thrust deflection ang

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36

Xu, Fu You, Bin Bin Li, Cai Liang Huang, and Zhe Zhang. "Experimental Research on Aerodynamic Characteristics of Bridge Deck at Extreme Attack Angles." Advanced Materials Research 163-167 (December 2010): 4104–8. http://dx.doi.org/10.4028/www.scientific.net/amr.163-167.4104.

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Long-span flexible bridges are always challenged by fierce wind load, and the wind with extreme-attack-angle may be a potential danger to threaten the bridge security. The three-component coefficients at extreme attack angles of the section model of one flat streamlined box-girder and central slotted box-girder are investigated through the wind tunnel test, and the detailed explanation are made. The results show that lift and pitch coefficients change approximately linearly between stall angles, and the coefficients display significant nonlinearity and a certain pulsation phenomenon when the a

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37

Erickson, G. E. "High Angle-of-Attack Aerodynamics." Annual Review of Fluid Mechanics 27, no. 1 (1995): 45–88. http://dx.doi.org/10.1146/annurev.fl.27.010195.000401.

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38

Stollery, J. L. "High angle of attack aerodynamics." Journal of Atmospheric and Terrestrial Physics 54, no. 11-12 (1992): 1646. http://dx.doi.org/10.1016/0021-9169(92)90172-h.

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39

Kadhem, Hassan Ali, and Ahmed Abdul Hussein. "The Effect of Attack Angle On The Vibration Suppression Of Composite Wing Airfoil NACA 0012." Association of Arab Universities Journal of Engineering Sciences 27, no. 4 (2021): 17–21. http://dx.doi.org/10.33261/https://doi.org/10.33261/jaaru.2020.27.4.003.

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Active vibration control is presented as an effective technique used for vibration suppression and for attenuating bad effects of disturbances on structure. In this work Proportional-Integral-Derivative control were employed to study suppression of active vibration wing affected by wind airflow. Two different composite wings with different manufacturing materials had been made with specific size to be suitable for using in wind tunnel. Piezoelectric (PZT (transducers are used as sensors and actuators in vibration control systems. The velocity was 25 m/s and three different attack angles (0, 10

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Tanasheva, N. K. "INVESTIGATION OF THE AERODYNAMIC FORCES OF A TRIANGULAR WIND TURBINE BLADE FOR THE LOW WIND SPEEDS." Eurasian Physical Technical Journal 18, no. 4 (38) (2021): 59–64. http://dx.doi.org/10.31489/2021no4/59-64.

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This article investigates the aerodynamic characteristics and finds the critical angle of attack of a triangular sail blade of a wind turbine for low wind speeds. For this purpose, a triangular sail blade of various parameters has been developed. The prototype is made of metal frame rods, the material of the triangular sail blade consists of a light and durable material (silk), one end of which is fixed to the top of the frame with a strong thread and support rods and bearing with an inner diameter of 8 mm. A sail blade differs from other blades in that the sails are made with the ability to c

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Liu, Qi, Juanmian Lei, Yong Yu, and Jintao Yin. "Effect of Bending Deformation on the Lateral Force of Spinning Projectiles with Large Aspect Ratio." Aerospace 10, no. 9 (2023): 810. http://dx.doi.org/10.3390/aerospace10090810.

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The bending deformation can affect the lateral force of spinning projectiles with large aspect ratios, thus interfering with their flight stability. Based on the established spin–deformation coupling motion model, the unsteady Reynolds averaged Navier–Stokes (URANS) equations are solved to simulate the flow over a large−aspect−ratio projectile undergoing spin and spin−deformation coupling motion by using the dual−time stepping method and dynamic mesh technique, obtaining the lateral force. Furtherly, the flow mechanism is analyzed for the changed lateral force induced by the bending deformatio

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Yun, Chenghu, and Danghui Liu. "Simulation and analysis of drag for inflatable aerodynamic decelerator." Journal of Physics: Conference Series 2489, no. 1 (2023): 012037. http://dx.doi.org/10.1088/1742-6596/2489/1/012037.

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Abstract Inflatable aerodynamic decelerator, as a novel deceleration and recovery technology, has received attention due to its lightweight and freedom from the launch vehicle fairing size constraints for the space mission. Aimed at the aerodynamic characteristics of the inflatable aerodynamic decelerator, this work studied the effect of the cone angle on its drag and discussed the drag varied with the angle of attack under the different cone angles. The simulation showed that the drag was affected by the cone angle and increased locally with the angle of attack. Furthermore, the larger cone a

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Ko, Arim, Kyoungsik Chang, Dong-Jin Sheen, Young-Hee Jo, and Ho Joon Shim. "CFD Analysis of the Sideslip Angle Effect around a BWB Type Configuration." International Journal of Aerospace Engineering 2019 (April 23, 2019): 1–14. http://dx.doi.org/10.1155/2019/4959265.

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In this study, we conducted numerical simulations for a nonslender BWB type planform with a rounded leading edge and span of 2.0 m to analyze the effect of the sideslip angle on the planform at a freestream velocity of 60 m/s. The Reynolds number based on the mean chord length was 2.9×106, and we considered the angle of attack ranging from -4° to 16° and sideslip angles up to 20°. We used an unstructured mesh with a prism layer for the boundary layer with 1.11×107 grid points, and the k−ω SST turbulence model. We analyzed force and moment coefficients with respect to variation of angle of atta

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Zhao, Xin-yang, and Kun Chen. "The investigation of lateral/heading characteristics and the influence of jet control at high attack angle." Journal of Physics: Conference Series 2478, no. 10 (2023): 102036. http://dx.doi.org/10.1088/1742-6596/2478/10/102036.

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Abstract When the aircraft does high maneuvers at a high attack angle, the rapid transition of flight state induces a series of complex flow phenomena such as flow separation and vortex breakdown, leading to a series of uncommanded motions such as self-excited roll oscillation, which brings great danger to the flight of the aircraft. Therefore, it is important to investigate the mechanism of this phenomenon and suppress it. In this paper, the numerical method is based on Lattice Boltzmann Method (LBM) and Large Eddy Simulation (LES) for the SACCON standard flying-wing layout aircraft model. Th

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Khalid, Mirza Haseeb. "CFD Analysis of NACA 0012 Aerofoil to Investigate the Effect of Increasing Angle of Attack on Coefficient of Lift and Coefficient of Drag." Journal of Studies in Science and Engineering 2, no. 1 (2022): 74–86. http://dx.doi.org/10.53898/josse2022216.

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The significance of using proper blade design is increasing with advancements in aviation technology. Wings are used in a variety of applications, including aircraft, drones, wind turbines, and more. In this study, Ansys version 2021 is used to do a CFD analysis on a NACA 0012 to study the effect of increasing the angle of attack on the coefficient of lift. Analyses have been performed using Ansys Fluent. The k-w turbulence model was used to analyze geometry, designed in SOLIDWORKS. At a speed of 32 m/s, several angles of attack have been evaluated from 0° to 20° to investigate lift and drag c

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Chen, Runpeng, and Yongqi Zhao. "The study the angle of attack and lift magnitude of a wing using COMSOL software." Theoretical and Natural Science 11, no. 1 (2023): 155–58. http://dx.doi.org/10.54254/2753-8818/11/20230398.

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Angle of attack (A.O.A.) is defined as the angle at which the chord of an aircrafts wing meets the relative wind. At low angles of attack, the wing could just create a small amount of lift, and it also experience a small amount of drag. As the A.O.A. increases, both lift and drag will increase. However, when the wing reaches a critical angle of attack, the lift it could produce will quickly decrease, since the separation of the air flow and the wing surface. The objective of this study is to find the relationship between the angle of attack and the lift coefficient(which is proportional to the

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Li, Xi, Feng Gao, Aojia Ma, and Dong Guo. "A rapid time-coordinated longitudinal guidance method for high-speed vehicle." Journal of Physics: Conference Series 2764, no. 1 (2024): 012072. http://dx.doi.org/10.1088/1742-6596/2764/1/012072.

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Abstract Compared to the traditional method of adjusting flight time by increasing lateral maneuverability [1-2], a faster time-coordinated longitudinal guidance method for unpowered high-speed vehicles has been proposed in this paper. Firstly, the centroid dynamics model and flight constraint model of unpowered high-speed vehicles were established, and the angle of attack corridor was derived based on quasi-equilibrium gliding conditions (QEGC). Then, to plan a reasonable angle of attack profile, the flight capability of a single vehicle under different constant angles of attack is analyzed,

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Li, Yuyan, Zheng Liu, Zhongqiu Wang, et al. "Study on the Hydrodynamic Performance of the Beam Used in the Antarctic Krill Beam Trawl." Fishes 9, no. 1 (2023): 17. http://dx.doi.org/10.3390/fishes9010017.

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The beam trawl is one of the primary operational trawls for Antarctic krill, and its beam provides horizontal expansion support for the trawl net. The hydrodynamic performance of the beam significantly affects the vertical expansion and sinking performance of the trawl, as well as impacts the energy consumption of the fishing vessel. In this study, the beam of the Antarctic krill trawl used on the “Shen Lan” fishing vessel served as a prototype. Three types of beams, cylindrical, airfoil, and elliptical, were designed. The hydrodynamic performances of beams with different shapes at different a

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Mahdi, Mohammed, and Yasser A. Elhassan. "Stability Analysis of a Light Aircraft Configuration Using Computational Fluid Dynamics." Applied Mechanics and Materials 225 (November 2012): 391–96. http://dx.doi.org/10.4028/www.scientific.net/amm.225.391.

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This work aims to simulate and study the flow field around SAFAT-01 aircraft using numerical solution based on solving Reynolds Averaged Navier-Stokes equations coupled with K-ω SST turbulent model. The aerodynamics behavior of SAFAT-01 aircraft developed at SAFAT aviation complex were calculated at different angles of attack and side slip angles. The x,y and z forces and moments were calculated at flight speed 50m/s and at sea level condition. Lift and drag curves for different angles of attack were plotted. The maximum lift coefficient for SAFAT-01 was 1.67 which occurred at angle of attack

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Kato, K., K. Hokkirigawa, T. Kayaba, and Y. Endo. "Three Dimensional Shape Effect on Abrasive Wear." Journal of Tribology 108, no. 3 (1986): 346–49. http://dx.doi.org/10.1115/1.3261193.

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The three dimensional shape effect of asperity on abrasive wear was investigated with in-situ experiments in the scanning electron microscope. The geometry of model asperity was represented by attack angle and dihedral angle, where attack angle changed in 0∼90 deg and dihedral angle in 0∼180 deg. Wear modes of shearing, cutting, and wedge forming were observed and each mode was related to attack angle and dihedral angle by wear mode diagram. Wear rate in cutting mode increased with attack angle and was maximum at a certain dihedral angle.

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