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Journal articles on the topic 'High angle of attack'

Author: Grafiati

Published: 4 June 2021

Last updated: 25 July 2025

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1

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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2

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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3

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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4

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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5

Anwar-ul-Haque, Ning Qin, and Farooq Umar. "ASYMMETRY OF FLOW AT HIGH ANGLE OF ATTACK(Compressible Flow)." Proceedings of the International Conference on Jets, Wakes and Separated Flows (ICJWSF) 2005 (2005): 661–66. http://dx.doi.org/10.1299/jsmeicjwsf.2005.661.

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6

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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7

Harloff, Gary J. "High angle-of-attack hypersonic aerodynamics." Journal of Spacecraft and Rockets 25, no. 5 (1988): 343–44. http://dx.doi.org/10.2514/3.26010.

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8

Dexter, P. C. "High Angle of Attack Missile Aerodynamics." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 207, no. 1 (1993): 15–19. http://dx.doi.org/10.1243/pime_proc_1993_207_241_02.

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A major influence in the aerodynamics of missiles is the significant amount of separated flow encountered for most flight conditions. This flow may be of an ordered nature, forming vortices, or random, such as encountered in wing stall. At high angles of attack the vortices of the body leeside flow may become unpredictably asymmetric, even on geometrically symmetric configurations, and their interactions with wing and tail panels can result in possible control problems. The modelling of such flows both accurately and easily is beyond present capabilities.

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9

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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10

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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11

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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12

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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13

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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14

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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15

Boyum, K. E., M. Pachter, and C. H. Houpis. "High angle of attack velocity vector rolls." Control Engineering Practice 3, no. 8 (1995): 1087–93. http://dx.doi.org/10.1016/0967-0661(95)00101-y.

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16

Boyum, Capt K. E., M. Pachter, and C. H. Houpis. "High Angle of Attack Velocity Vector Rolls." IFAC Proceedings Volumes 27, no. 13 (1994): 53–59. http://dx.doi.org/10.1016/s1474-6670(17)45778-8.

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17

ZHAO, ZIJIE, CHAO GAO, FENG LIU, and SHIJUN LUO. "PLASMA FLOW CONTROL OVER FOREBODY AT HIGH ANGLES OF ATTACK." Modern Physics Letters B 24, no. 13 (2010): 1405–8. http://dx.doi.org/10.1142/s0217984910023736.

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Forward blowing from a pair of plasma actuators on the leeward surface and near the apex is used to switch the asymmetric vortex pair over a cone of semi-apex angle 10° at high angles of attack. Wind tunnel pressure measurements show that by appropriate design of the actuators and appropriate choice of the AC voltage and frequency, side forces and yawing moments of opposite signs can be obtained at a given angle of attack by activating one of the plasma actuators. Further work is suggested.

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18

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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19

WANG, Yifei, Jianjun DANG, Chuang HUANG, Haiyu XU, and Zhenhao ZUO. "Influence of attack angle on ventilated supercavitating flow at high Froude number condition." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 40, no. 6 (2022): 1233–41. http://dx.doi.org/10.1051/jnwpu/20224061233.

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To study the influence of attack angle on ventilated supercavitating flow, a numerical model is established to simulate the supercavitation flow by using the inhomogeneous multiphase flow model and the SST k-ω turbulence model. And then, the model is verified and validated by comparing with the experimental results. The effect of attack angle on the profile of ventilated supercavity was numerically investigated over high Froude number. Results show that the attack angle causes the linear deviation of the ventilated supercavity axis, the deviation angle is in direct proportion to the attack ang

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20

Tingting, Yang, Li Aijun, Muhammad Taimoor, and Rooh ul Amin. "High AOA short landing robust control for an aircraft." Aircraft Engineering and Aerospace Technology 91, no. 1 (2018): 38–49. http://dx.doi.org/10.1108/aeat-05-2017-0134.

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Purpose The purpose of this paper is to propose a high angle of attack short landing model for switched polytopic systems as well as to derive an equation for fluidic thrust vector deflection angle based on pressure to reduce the velocity during the landing phase of flight. Design/methodology/approach In this paper, robust control algorithm is proposed for a non-linear high angle of attack aircraft under the effects of non-linearities, tottering hysteresis, irregular and wing rock atmosphere. High angle of attack short landing flight under asynchronous switching is attained by using the robust

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21

Whitmore, Stephen A., Timothy R. Moes, and Terry J. Larson. "High angle-of-attack flush airdata sensing system." Journal of Aircraft 29, no. 5 (1992): 915–19. http://dx.doi.org/10.2514/3.46262.

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22

Kleb, William L., and K. James Weilmuenster. "High angle-of-attack inviscid Shuttle Orbiter computation." Journal of Spacecraft and Rockets 29, no. 5 (1992): 746–48. http://dx.doi.org/10.2514/3.11520.

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23

Bai, Chenyuan, and Ziniu Wu. "Hypersonic starting flow at high angle of attack." Chinese Journal of Aeronautics 29, no. 2 (2016): 297–304. http://dx.doi.org/10.1016/j.cja.2016.02.008.

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24

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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25

Zeng, Qingsong, Wei Cai, and Junhui Xu. "Large-Eddy Simulation of Low-Frequency Flow Oscillations for NACA0012 and Dynarig Sail at Large Attack Angles." Journal of Marine Science and Engineering 12, no. 5 (2024): 835. http://dx.doi.org/10.3390/jmse12050835.

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Unmanned sailboats, harnessing wind for propulsion, offer great potential for extended marine research due to their virtually unlimited endurance. The sails typically operate at high attack angles, which contrasts with aircraft that maintain small angles to prevent stalling. Despite the reduction in lift during stalling, the resultant increase in drag contributes significantly to the sail’s thrust. However, the sail often experiences vortex shedding due to high attack angles, leading to low-frequency oscillations and erratic navigation. This study employs large-eddy simulations (LESs) on a 3D

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26

Schettini, Francesco, Gianpietro Di Rito, and Eugenio Denti. "Aircraft flow angles calibration via observed-based wind estimation." Aircraft Engineering and Aerospace Technology 91, no. 7 (2019): 1033–38. http://dx.doi.org/10.1108/aeat-06-2017-0145.

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Purpose This paper aims to propose a novel approach, in which the reference data for the flow angles calibration are obtained by using measurements coming from an inertial navigation system and an air data sensor. Design/methodology/approach This is obtained by using the Kalman filter theory for the evaluation of the reference angle-of-attack and angle-of-sideslip. Findings The designed Kalman filter has been implemented in Matlab/Simulink and validated using flight data coming from two very different aircraft, the Piaggio Aerospace P1HH medium altitude long endurance unmanned aerial system an

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27

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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ElAwad, Yasir A., and Eltayeb M. ElJack. "Numerical investigation of the low-frequency flow oscillation over a NACA-0012 aerofoil at the inception of stall." International Journal of Micro Air Vehicles 11 (January 2019): 175682931983368. http://dx.doi.org/10.1177/1756829319833687.

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High-fidelity large eddy simulation is carried out for the flow field around a NACA-0012 aerofoil at Reynolds number of [Formula: see text], Mach number of 0.4, and various angles of attack around the onset of stall. The laminar separation bubble is formed on the suction surface of the aerofoil and is constituted by the reattached shear layer. At these conditions, the laminar separation bubble is unstable and switches between a short bubble and an open bubble. The instability of the laminar separation bubble triggers a low-frequency flow oscillation. The aerodynamic coefficients oscillate acco

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29

Thanh, Bui The, and Ngo Kien Trung. "Using the Model Reduction Techniques to Find the Low-Order Controller of the Aircraft's Angle of Attack Control System." Journal Européen des Systèmes Automatisés 55, no. 5 (2022): 649–55. http://dx.doi.org/10.18280/jesa.550510.

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The problem of controlling the angle of attack of the aircraft is one of the difficult and complex problems due to the problems of nonlinear kinematics, variable parameters and uncertainty model. The design of the angle of attack control according to the robustness control algorithm often leads to a higher order robustness controller. Using a higher-order controller has many disadvantages, so it is necessary to have solutions to reduce the order of the controller. This paper presents the idea of designing a low-order controller for the aircraft's angle of attack control system using the order

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30

Wang, Yeguang, Shitong Jian, Zhigang Wang, Rui Fan, Peng Han, and Yongxi Lyu. "An Intelligent Algorithm for Aerodynamic Parameters Calibration of Wind Tunnel Experiment at a High Angle of Attack." International Journal of Aerospace Engineering 2023 (January 7, 2023): 1–15. http://dx.doi.org/10.1155/2023/3093526.

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In this paper, an intelligent algorithm for the aerodynamic parameter calibration of wind tunnel experiments of advanced layout aircraft at a high angle of attack is proposed. The proposed algorithm is based on a homologous comparison and tuning algorithm, and it can effectively improve the accuracy of the wind tunnel experiment model. First, based on the analysis of large oscillation wind tunnel experimental data of an advanced layout scaled aircraft, the high angle of attack wind tunnel experimental model composed of static derivative, dynamic derivative, and rotating balance derivative is e

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31

Xiang, Guo, Yongpeng Ou, Junjie Chen, Wei Wang, and Hao Wu. "Numerical Study on the Flow Characteristics of High Attack Angle around the Submarine’s Vertical Plane." Applied Sciences 14, no. 1 (2023): 395. http://dx.doi.org/10.3390/app14010395.

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When a submarine encounters an emergency situation, it should take emergency-surfacing actions by moving upward with a large angle of attack in the vertical plane. Previous research has often neglected the effect of vertical plane motion on the lateral force (Fy), rolling moment (Mx), and yawing moment (Mz). To examine the flow characteristics of submarines at high angles of attack on the vertical plane, the SST-DDES method is adopted in conjunction with adaptive mesh refinement (AMR) technology, and the new Omega vortex detection method is employed as the AMR criterion for numerical calculati

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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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FAN, ZHAO LIN, YUAN JING WANG, and QUAN ZHOU LU. "ANALYSIS OF UNSTEADY CHARACTERISTICS OF THE FLOW FIELD AT HIGH ANGLE OF ATTACK." Modern Physics Letters B 19, no. 28n29 (2005): 1583–86. http://dx.doi.org/10.1142/s0217984905009961.

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Energy components in the flow field at high angle of attack were analyzed by the dynamic measurement. The effect of the unsteadiness induced by these components on the flow was analyzed as well. The results showed that the flow itself at high angle of attack is a kind of "vortices behavior" and the effect of unsteadiness on the asymmetry of flow is relatively weak. The key factor that can essentially affect the flow at high angle of attack is the response of the dynamic unsteadiness of the vortices to the unpredictable micro-disturbance coming from near the nose of the model.

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34

Gao, Na, and WeidongYang. "Influence of Low Speed and High Angle of Attack on Sting Support Interference." Journal of Physics: Conference Series 2457, no. 1 (2023): 012042. http://dx.doi.org/10.1088/1742-6596/2457/1/012042.

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Abstract In order to improve the quality of low-speed and high angle of attack test data and master the law of support interference, a numerical simulation study of support interference was carried out for a wind tunnel tensioning tail brace system. The results show that the impact of the beam of wire-assistant sting support on longitudinal aerodynamics characteristics of aircraft is small, and the “E” sting greatly affects longitudinal aerodynamics characteristics at a high angle of attack. The yawing moment coefficients decrease, and rolling moment coefficients increase at the angle of attac

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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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Cleaver, D. J., Z. Wang, and I. Gursul. "Bifurcating flows of plunging aerofoils at high Strouhal numbers." Journal of Fluid Mechanics 708 (August 8, 2012): 349–76. http://dx.doi.org/10.1017/jfm.2012.314.

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AbstractForce and particle image velocimetry measurements were conducted on a NACA 0012 aerofoil undergoing small-amplitude high-frequency plunging oscillation at low Reynolds numbers and angles of attack in the range 0–$2{0}^{\ensuremath{\circ} } $. For angles of attack less than or equal to the stall angle, at high Strouhal numbers, significant bifurcations are observed in the time-averaged lift coefficient resulting in two lift-coefficient branches. The upper branch is associated with an upwards deflected jet, and the lower branch is associated with a downwards deflected jet. These branches

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Huang, Han Jie, and Xin Min Li. "Experimental Study on the Influence Factors of Static Aerodynamic Characteristics of Ice-Coated Commonly Used Conductors." Advanced Materials Research 774-776 (September 2013): 1227–31. http://dx.doi.org/10.4028/www.scientific.net/amr.774-776.1227.

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For conductors commonly used in the high and ultra-high voltage transmission projects, research was conducted on how ice shape, ice thickness, wind speed and angle of attack affect the static aerodynamic characteristics of ice-coated conductor. The ice shape and the shape of ice-coated conductor are both important factors that determine the aerodynamic characteristics of conductor. Sudden increase of lift coefficient may happen at low angle of attack. Wind speed shows less effect on aerodynamic characteristics of ice-coated conductor with streamlined shape than that of conductor with blunt sha

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38

Durham, Wayne C. "Control stick logic in high-angle-of-attack maneuvering." Journal of Guidance, Control, and Dynamics 18, no. 5 (1995): 1092–97. http://dx.doi.org/10.2514/3.21509.

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Cummings, Russell M., James R. Forsythe, Scott A. Morton, and Kyle D. Squires. "Computational challenges in high angle of attack flow prediction." Progress in Aerospace Sciences 39, no. 5 (2003): 369–84. http://dx.doi.org/10.1016/s0376-0421(03)00041-1.

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40

Cho, S., and K. R. Cho. "Nonlinear adaptive control for high angle of attack flight." KSME Journal 9, no. 2 (1995): 147–55. http://dx.doi.org/10.1007/bf02953616.

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41

M. Rouyan, Nurhana, Renuganth Varatharajoo, Samira Eshghi, Ermira Junita Abdullah, and Shinji Suzuki. "Aircraft pitch control tracking with sliding mode control." International Journal of Engineering & Technology 7, no. 4.13 (2018): 62. http://dx.doi.org/10.14419/ijet.v7i4.13.21330.

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Sliding mode control (SMC) is one of the robust and nonlinear control methods. An aircraft flying at high angles of attack is considered nonlinear due to flow separations, which cause aerodynamic characteristics in the region to be nonlinear. This paper presents the comparative assessment for the flight control based on linear SMC and integral SMC implemented on the nonlinear longitudinal model of a fighter aircraft. The controller objective is to track the pitch angle and the pitch rate throughout the high angles of attack envelope. Numerical treatments are carried out on selected conditions

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Liu, Hui, Jin Yun Pu, Qi Xiu Li, and Xiang Jun Wu. "The Analysis of Flooded Submarine Motion State Varying from Different Attack Angle under Blowing Ballast Tank." Applied Mechanics and Materials 336-338 (July 2013): 442–45. http://dx.doi.org/10.4028/www.scientific.net/amm.336-338.442.

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The paper establishes emergency recovery maneuver model of six degree of freedom and blowing ballast compartment model of high pressure air. Based on standard maneuver equation, considering the influence of large angle of attack to hydrodynamics coefficient, correct the standard equation through supplementing hydrodynamics items. Applying large and small angle of attack system to simulate and calculate state parameters, and find the occasion of large of attack, the influence of initialization velocity and depth to change of angle of attack. The results prove that large angle of attack system i

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DUDLEY, R., and C. P. ELLINGTON. "Mechanics of Forward Flight in Bumblebees: I. Kinematics and Morphology." Journal of Experimental Biology 148, no. 1 (1990): 19–52. http://dx.doi.org/10.1242/jeb.148.1.19.

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Using high-speed cinematography, bumblebees in free flight were filmed over a range of forward airspeeds. A detailed description of the wing tip and body kinematics was obtained from a three-dimensional reconstruction of the twodimensional film image. A technique for determining quantitatively the angle of attack of the wing was developed. Kinematic parameters found to vary consistently with airspeed were body angle, stroke plane angle, geometrical angle of attack, and rotational angles of the wings at the ends of half-strokes. Results of a morphological analysis of the wings and bodies of tho

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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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Wafi, A., M. H. Basha, M. Tasyrif, and M. F. Hamid. "Aerodynamics Analysis of UniMAP Automotive Racing Team Formula SAE Race Car spoiler via Simulation: Effect of Angle of Attack." Journal of Physics: Conference Series 2051, no. 1 (2021): 012021. http://dx.doi.org/10.1088/1742-6596/2051/1/012021.

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Abstract When a racing car moves at high velocity, aerodynamic factors will cause a lift and drag force, causing the speeding vehicle to lose stability, traction and speed. To solve this problem, racing cars use a rear spoiler as a medium to reduce drag and lift, increasing the car’s stability. This study explores the idea that focuses on the impact of the angle of attack on UniART SAE race car performance and the effect of angle of attack on drag force and downforce. ANSYS Fluent is used to generate the simulation In the context of the lift force analysis, angle of attack equal to 12.5° produ

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Mori, Masaaki. "Numerical Simulation of Aeroacoustics Generated by Flow around 30P30N High-lift Aerofoil using Hybrid CFD/BEM approach." INTER-NOISE and NOISE-CON Congress and Conference Proceedings 267, no. 1 (2023): 338–42. http://dx.doi.org/10.3397/no_2023_0083.

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In this study, we have performed the acoustic simulation generated by the flow around the 30P30N airfoil with a slat and a flap by means of Boundary element Method using quadrupole sources extracted from the unsteady CFD simulations. The CFD simulations are performed using Ansys Fluent with LES Dynamic Model, and compressible flow fields have been solved. The attack angles of the airfoil are 5.5 and 9.5 degree. When the BEM calculation for the acoustic propagation was performed, the FMM (Fast Multipole Method) and FMBEM were used to calculate quickly the contributions from the quadrupole sourc

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Said, M., M. Imai, S. Mat, et al. "Tuft Flow Visualisation on UTM-LST VFE-2 Delta Wing Model Configuration at High Angle of Attacks." International Journal of Automotive and Mechanical Engineering 17, no. 3 (2020): 8214–23. http://dx.doi.org/10.15282/ijame.17.3.2020.15.0619.

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This paper reports on flow visualisation and surface pressure measurements over the upper surface of a blunt-edged delta wing model at high angles of attack. The flow structure above the upper surface of the blunt-edged delta wing was found to be different compared to delta wing with sharp leading edge. The flow becomes more complicated especially in the leading edge region of the wing. Currently, there is no data available to verify if the primary vortex could reach the apex of the wing when the angle of attack is further increased. Most prior experiments were performed at the angles of attac

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Brunton, Steven L., Clarence W. Rowley, and David R. Williams. "Reduced-order unsteady aerodynamic models at low Reynolds numbers." Journal of Fluid Mechanics 724 (April 29, 2013): 203–33. http://dx.doi.org/10.1017/jfm.2013.163.

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AbstractIn this paper we develop reduced-order models for the unsteady lift on a pitching and plunging aerofoil over a range of angles of attack. In particular, we analyse the pitching and plunging dynamics for two cases: a two-dimensional flat plate at $\mathit{Re}= 100$ using high-fidelity direct numerical simulations and a three-dimensional NACA 0006 aerofoil at $\mathit{Re}= 65\hspace{0.167em} 000$ using wind-tunnel measurements. Models are obtained at various angles of attack and they are verified against measurements using frequency response plots and large-amplitude manoeuvres. These mo

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Li, Yadong, Junyao Zhang, Fengtian Yang, and Yongliang Chen. "Research on high attack angle stall and spin characteristics with flight test of a general electric aircraft." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 39, no. 3 (2021): 650–59. http://dx.doi.org/10.1051/jnwpu/20213930650.

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When the aircraft is flying at high angle of attack, the local separation of the air flow on the surface of the aircraft, the linear change of aerodynamic force is destroyed, and the maneuverability and stability are reduced to varying degrees, resulting in the aircraft stalling or entering the spin. The stall characteristics and spin characteristics directly affect the safety of the aircraft. In order to analyze the stall and spin characteristics, a full-scale 6-DOF nonlinear high angle of attack dynamic model is established for a two-seater electric high aspect ratio aircraft based on the wi

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SUN, Huixun, Pengpeng SUN, Yongfei YANG, Mingchuan YUAN, Feng FAN, and Yongfeng LIN. "Analysis of aerodynamic characteristics of helicopter biplane tailplane." Xibei Gongye Daxue Xuebao/Journal of Northwestern Polytechnical University 42, no. 2 (2024): 232–40. http://dx.doi.org/10.1051/jnwpu/20244220232.

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To analyze the aerodynamic characteristics of helicopter biplane tailplane, computational models for helicopter biplane tailplane and monoplane tailplane were established via CFD. The aerodynamic characteristics of different configurations of tailplanes at low speed forward flight and high angle of attack was obtained. The aerodynamic characteristics and flow characteristics of biplane/monoplane tailplane were analyzed. The mechanism of biplane tailplane to improve the longitudinal static stability at low speed forward flight and high angle of attack was investigated. The results show that the

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