Log in

Relevant bibliographies by topics / High angle of attack / Journal articles

Journal articles on the topic 'High angle of attack'

To see the other types of publications on this topic, follow the link: High angle of attack.

Author: Grafiati

Published: 4 June 2021

Last updated: 19 February 2022

Create a spot-on reference in APA, MLA, Chicago, Harvard, and other styles

Select a source type:

Consult the top 50 journal articles for your research on the topic 'High angle of attack.'

Next to every source in the list of references, there is an 'Add to bibliography' button. Press on it, and we will generate automatically the bibliographic reference to the chosen work in the citation style you need: APA, MLA, Harvard, Chicago, Vancouver, etc.

You can also download the full text of the academic publication as pdf and read online its abstract whenever available in the metadata.

Browse journal articles on a wide variety of disciplines and organise your bibliography correctly.

1

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.

Full text

APA, Harvard, Vancouver, ISO, and other styles

2

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

Full text

APA, Harvard, Vancouver, ISO, and other styles

3

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

Full text

APA, Harvard, Vancouver, ISO, and other styles

4

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.

Full text

Abstract:

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 application scopes of the formulas of lift and drag coefficients were given. Final, the relations of lift and drag coefficients were obtained by eliminating all angles of attack. Research results show that lift - drag curve of small angles of attack is parabola, and the lift - drag curve of high angles of attack is circle.

APA, Harvard, Vancouver, ISO, and other styles

5

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

Full text

APA, Harvard, Vancouver, ISO, and other styles

6

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 (January 1993): 15–19. http://dx.doi.org/10.1243/pime_proc_1993_207_241_02.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

7

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.

Full text

Abstract:

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 force direction did not change with the change of the altitude and the angle of attack at low angles of attack; however, it changed with altitude at an angle of attack of 30°. When the angle of attack was 20°, the interference of the tail fin to the lateral force of the missile body was different from that for other angles of attack, leading to an increase of the lateral force of the rear part of the missile body. With the increasing altitude, the position of the boundary layer with a larger thickness of the missile body moved forward, making the lateral force distribution of the missile body even. Consequently, Magnus moments generated by different boundary layer thicknesses at the front and rear of the missile body decreased and the Magnus moment generated by the tail fin became larger. As lateral force directions of the missile body and the tail were opposite, the Magnus moment direction changed noticeably. Under a high angle of attack, the Magnus moment direction of the missile body changed with the increasing altitude. The absolute value of the pitch moment coefficient of the missile body decreased with the increasing altitude.

APA, Harvard, Vancouver, ISO, and other styles

8

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 (June 3, 2020): 2040124. http://dx.doi.org/10.1142/s0217979220401244.

Full text

Abstract:

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 rather than the upper surface. This paper proposes another explanation that the nonlinear lift increase is related to the attachment of shock wave, influenced by the leading-edge sweep angle. The shock wave is more inclined to attach under the lower surface with smaller swept than that of larger swept as angle of attack increases. When the shock wave attaches, the pressure increase via angle of attack is nonlinear, leading to the nonlinearity of lift increase.

APA, Harvard, Vancouver, ISO, and other styles

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.

Full text

Abstract:

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 aerodynamic derivative terms that have higher-order polynomials for these values. The improved nonlinear aerodynamic derivative model was validated by using the NACA 0015 airfoil and the F-18 model. The results show that the improved model has a higher prediction ability at high angles of attack and has the ability to predict the aerodynamic characteristics of other unknown states based on known unsteady aerodynamic data, such as the initial angle of attack, reduced frequency, and oscillation amplitude.

APA, Harvard, Vancouver, ISO, and other styles

10

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

Full text

APA, Harvard, Vancouver, ISO, and other styles

11

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

Full text

APA, Harvard, Vancouver, ISO, and other styles

12

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 (May 26, 2021): 131–44. http://dx.doi.org/10.31763/ijrcs.v1i2.329.

Full text

Abstract:

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 the LQR and SDRE controllers were able to smooth the flight response maintaining conditions in balance for an angle of attack up to 56% above stall angle. However, for even more difficult situations, with angles of attack up to 76% above the stall angle, only the SDRE controller proved to be efficient and reliable in recovering the aircraft to its stable flight configuration.

APA, Harvard, Vancouver, ISO, and other styles

13

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 (May 30, 2010): 1405–8. http://dx.doi.org/10.1142/s0217984910023736.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

14

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

Full text

APA, Harvard, Vancouver, ISO, and other styles

15

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

Full text

APA, Harvard, Vancouver, ISO, and other styles

16

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

Full text

APA, Harvard, Vancouver, ISO, and other styles

17

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 (October 22, 2019): 4021. http://dx.doi.org/10.3390/en12204021.

Full text

Abstract:

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. First, the airfoil was fixed at a constant angle of attack to analyze the aerodynamic characteristics and the hydrodynamic moment. Second, the angle of attack of airfoils was passively changed by the fluid force to analyze the attitude stability. The current numerical solver for the flow field around an unsteady rotating airfoil was validated against the published numerical data. It was confirmed that the corrugated airfoil performs (in terms of the lift-to-drag ratio) much better than the profiled NACA2408 airfoil at low Reynolds number R e = 4000 in low angle of attack range of 0 ∘ – 6 ∘ , and performs as well at the angle of attack of 6 ∘ or more. At these low angles of attack, the corrugated airfoil experiences an increase in the pressure drag and decrease in shear drag due to recirculation zones inside the cavities formed by the pleats. Furthermore, the increase in the lift for the corrugated airfoil is due to the negative pressure produced at the valleys. It was found that the lift and drag in the 2D numerical calculation are strong fluctuating at a high angle of attacks. However, in 3D simulation, especially for a 3D corrugated airfoil with unevenness in the spanwise direction, smaller fluctuations and the smaller average value in the lift and drag were obtained than the results in 2D calculations. It was found that a 3D wing with irregularities in the spanwise direction could promote three-dimensional flow and can suppress lift fluctuations even at high angles of attack. For the attitude stability, the corrugated airfoil is statically more unstable near the angle of attack of 0 ∘ , has a narrower static stable range of the angle of attack, and has a larger amplitude of fluctuations of the angle of attack compared with the profiled NACA2408 airfoil. Based on the Routh–Hurwitz stability criterion, it was confirmed that the control systems of the angle of attack passively changed by the fluid force for both two airfoils are unstable systems.

APA, Harvard, Vancouver, ISO, and other styles

18

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 (January 7, 2018): 38–49. http://dx.doi.org/10.1108/aeat-05-2017-0134.

Full text

Abstract:

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 controller method. Lyapunov function and the average dwell time scheme is used for obtaining the switched polytopic scheme. The asynchronous switching and loss of data are controlled asymptotically. The velocity of aircraft has been lucratively reduced during the landing phase of flight by using the robust controller technique. Findings The proposed algorithm based on robust controller including the effects of non-linearities guarantee the successful reduction of velocity for high angle of attack switched polytopic systems. Practical implications As the landing phase of an aircraft is one of the complicated stage, this algorithm plays a vital role in stable and short landing under the condition of high angle of attack (AOA). Originality/value In this paper, not only the velocity of flight has been reduced, but also the high angle of attack has been attained during the landing phase, because of which the duration of landing has been reduced as well, while in most of the previous research, it is based on low angle of attack and long landing duration.

APA, Harvard, Vancouver, ISO, and other styles

19

Lacagnina, Giovanni, Paruchuri Chaitanya, Jung-Hoon Kim, Tim Berk, Phillip Joseph, Kwing-So Choi, Bharathram Ganapathisubramani, 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 (February 1, 2021): 130–56. http://dx.doi.org/10.1177/1475472x20978379.

Full text

Abstract:

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 attack (AoA) regimes: low angles where the flow is mostly attached, moderate angles where the flow is partially to fully separated, and high angles of attack where the flow is fully separated. Leading edge serrations have been demonstrated to be effective in reducing noise at low and high angles of attack but ineffective at moderate angles. The noise reduction mechanisms are explored in each of three angle regimes.

APA, Harvard, Vancouver, ISO, and other styles

20

PrabhakaraRao, Dr P., and Sri Sampath V. "CFD Analysis on Airfoil at High Angles of Attack." International Journal of Engineering Research 3, no. 7 (July 1, 2014): 430–34. http://dx.doi.org/10.17950/ijer/v3s7/704.

Full text

APA, Harvard, Vancouver, ISO, and other styles

21

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 (July 2003): 369–84. http://dx.doi.org/10.1016/s0376-0421(03)00041-1.

Full text

APA, Harvard, Vancouver, ISO, and other styles

22

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

Full text

APA, Harvard, Vancouver, ISO, and other styles

23

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

Full text

APA, Harvard, Vancouver, ISO, and other styles

24

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 (December 20, 2005): 1583–86. http://dx.doi.org/10.1142/s0217984905009961.

Full text

Abstract:

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.

APA, Harvard, Vancouver, ISO, and other styles

25

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 (July 8, 2019): 1033–38. http://dx.doi.org/10.1108/aeat-06-2017-0145.

Full text

Abstract:

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 and the Alenia-Aermacchi M346 Master™ transonic trainer. This paper illustrates some results where the filter satisfactory behaviour is verified by comparing the filter outputs with the data coming from high-accuracy nose-boom vanes. Practical implications The methodology aims to lower the calibration costs of the air data systems of an advanced aircraft. Originality/value The calibration of air-data systems for the evaluation of the flow angles is based on the availability of high-accuracy reference measurements of angle-of-attack and angle-of-sideslip. Typically, these are obtained by auxiliary sensors directly providing the reference angles (e.g. nose-boom vanes). The proposed methodology evaluates the reference angle-of-attack and angle-of-sideslip by analytically reconstructing them using calibrated airspeed measurements and inertial data.

APA, Harvard, Vancouver, ISO, and other styles

26

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.

Full text

Abstract:

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 are stable and highly repeatable, and are achieved by increasing or decreasing the frequency in the experiments. Increasing frequency refers to starting from stationary and increasing the frequency very slowly (while waiting for the flow to reach an asymptotic state after each change in frequency); decreasing frequency refers to impulsively starting at the maximum frequency and decreasing the frequency very slowly. For the latter case, angle of attack, starting position and initial acceleration rate are also parameters in determining which branch is selected. The bifurcation behaviour is closely related to the properties of the trailing-edge vortices. The bifurcation was therefore not observed for very small plunge amplitudes or frequencies due to insufficient trailing-edge vortex strength, nor at larger angles of attack due to greater asymmetry in the strength of the trailing-edge vortices, which creates a preference for a downward deflected jet. Vortex strength and asymmetry parameters are derived from the circulation measurements. It is shown that the most appropriate strength parameter in determining the onset of deflected jets is the circulation normalized by the plunge velocity.

APA, Harvard, Vancouver, ISO, and other styles

27

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.

Full text

Abstract:

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 accordingly at a low frequency. The lift and the drag coefficients compare very well to recent high-accuracy experimental data, and the lift leads the drag by a phase shift of [Formula: see text]. The mean lift coefficient peaks at the angle of attack of [Formula: see text], in total agreement with the experimental data. The spectra of the lift coefficient does not show a significant low-frequency peak at angles of attack lower than or equal the stall angle of attack ([Formula: see text]). At higher angles of attack, the spectra show two low-frequency peaks and the low-frequency flow oscillation is fully developed at the angle of attack of [Formula: see text]. The behaviour of the flow-field and changes in the turbulent kinetic energy over one low-frequency flow oscillation cycle are described qualitatively.

APA, Harvard, Vancouver, ISO, and other styles

28

Said, M., M. Imai, S. Mat, M. N. Dahalan, S. Mansor, M. N. Mohd Nasir, and N. A. R. Nik Mohd. "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 (October 7, 2020): 8214–23. http://dx.doi.org/10.15282/ijame.17.3.2020.15.0619.

Full text

Abstract:

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 attack, α, below 23° with only a few experiments that had gone to α = 27°. These prior experiments and some CFD works stipulated that the attached flow continue to exist in the apex region of the delta wing even at very high angles of attack above 23°. In order to verify this hypothesis, several experiments at high angles of attack were conducted in Universiti Teknologi Malaysia Low Speed wind Tunnel (UTM–LST), using a specially constructed VFE2 wing model equipped with blunt leading edges. This series of experiments employed two measurement techniques; the first was the long tuft flow visualisation method, followed by surface pressure measurements. The experiments were performed at Reynolds numbers of 1.0×106 and 1.5×106. During these experiments, several interesting flow characteristics were observed at high angles of attack, mainly that the flow became more sensitive to changes in Reynolds number and the angles of attack of the wing. When the Reynolds number increased from 1×106 to 1.5×106, the upstream progression of the initial point of the main vortex was relatively delayed compared to the sharp-edged delta wing. The experiments also showed that the flow continued to be attached in the apex region up to α = 27º.

APA, Harvard, Vancouver, ISO, and other styles

29

Ye, Zheng-Yin, and Ling-Cheng Zhao. "Localized linearization method for wings at high angle of attack." AIAA Journal 28, no. 10 (October 1990): 1820–22. http://dx.doi.org/10.2514/3.10479.

Full text

APA, Harvard, Vancouver, ISO, and other styles

30

Hodgkin, F., and N. J. Wood. "Forebody Flow Control for Extended High-Angle-of-Attack Maneuvers." Journal of Aircraft 35, no. 2 (March 1998): 212–17. http://dx.doi.org/10.2514/2.2310.

Full text

APA, Harvard, Vancouver, ISO, and other styles

31

Taylor, G. S., I. Gursul, and D. I. Greenwell. "Investigation of Support Interference in High-Angle-of-Attack Testing." Journal of Aircraft 40, no. 1 (January 2003): 143–52. http://dx.doi.org/10.2514/2.3069.

Full text

APA, Harvard, Vancouver, ISO, and other styles

32

Font, S., H. Siguerdidjane, and E. Devaud. "Some Control Strategies of High Angle of Attack Missile Autopilot." IFAC Proceedings Volumes 31, no. 21 (August 1998): 53–58. http://dx.doi.org/10.1016/s1474-6670(17)41058-5.

Full text

APA, Harvard, Vancouver, ISO, and other styles

33

Favier, D., C. Maresca, A. Castex, and C. Barbi. "Vortex influence on oscillating airfoils at high angle of attack." Journal of Aircraft 24, no. 7 (July 1987): 424–32. http://dx.doi.org/10.2514/3.45497.

Full text

APA, Harvard, Vancouver, ISO, and other styles

34

Ye, Zheng-yin, and Ling-cheng Zhao. "Nonlinear flutter analysis of wings at high angle of attack." Journal of Aircraft 31, no. 4 (July 1994): 973–74. http://dx.doi.org/10.2514/3.46587.

Full text

APA, Harvard, Vancouver, ISO, and other styles

35

Visser, H. G. "Optimization of High Angle-of-Attack Approach to Landing Trajectories." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 219, no. 6 (June 1, 2005): 497–506. http://dx.doi.org/10.1243/095441005x33394.

Full text

Abstract:

The use of thrust vectoring technologies for performing extremely short takeoff and landing (ESTOL) operations was recently successfully demonstrated in a series of flight experiments involving an X-31 aircraft. The study presented herein builds on these ESTOL developments. More specifically, the main goal of the present study is to shape high angle-of-attack approach trajectories in such a way that starting at a given altitude and speed, the down-range distance to the runway threshold is minimized. In other words, the steepest approach possible is explored. The approach-to-landing problem is formulated as an optimal control problem and solved numerically, using a rigid-body model of a thrust-vectored version of an F-16 fighter aircraft. The employed numerical method, collocation with non-linear programming, proves well suited for solving this problem.

APA, Harvard, Vancouver, ISO, and other styles

36

Buffington, J. M., and R. J. Adams. "Nonlinear vortex flow control for high-angle-of-attack maneuvering." Control Engineering Practice 3, no. 5 (May 1995): 631–42. http://dx.doi.org/10.1016/0967-0661(95)00039-w.

Full text

APA, Harvard, Vancouver, ISO, and other styles

37

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.

Full text

Abstract:

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 attack and sideslip angles. Side force and rolling/yawing moment coefficients had highly nonlinear relationships with the sideslip angle while lift and drag coefficients were not significantly affected. We interpreted the mechanism of these aerodynamic characteristics based on pressure and skin friction contours. Suction pressure near the leading edge had a marked effect on the pitching and rolling moment. We identified five flow types on the blunt leading edge swept wing by skin friction lines and off-body streamlines at a high angle of attack and sideslip angles.

APA, Harvard, Vancouver, ISO, and other styles

38

Ge, Chang Jiang, and Mei Chen Ge. "High-Lift Mechanism of a Bionic Slat." Applied Mechanics and Materials 461 (November 2013): 220–29. http://dx.doi.org/10.4028/www.scientific.net/amm.461.220.

Full text

Abstract:

To avoid broadband noise from a slat cove, the deployed slat contour is usually modified by filling cove, but the design is sensitive to aerodynamic performance. In the paper, a bionic slat without a cove is built on the basis of a bionic airfoil (i.e. stowed bionic multi-element airfoil), which is extracted from a long-eared owl wing. The quasi-two-dimensional models with a deployed bionic slat and a stowed bionic slat are manufactured by rapid manufacturing and prototyping system, respectively, and measured in a low-turbulence wind tunnel. The results are used to characterize high-lift effect: the lift coefficients of the model with a stowed slat are larger at less than 4°angle of attack, but the model with a deployed slat has the larger lift coefficients at greater than 4°angle of attack. Furthermore, the deployed bionic slat can increase stall angle and maximum lift coefficient, but also delay the decline of the lift coefficient curve slope meaning that the leading-edge separation is postponed within a certain range of angle of attack. At the same time, the flow field around the models is visualized by smoke wire method. The leading-edge separation of the model with a stowed slat is shown at low Reynolds number and angle of attack. However, the finding does not occur in the flow field of the model with a deployed slat at the same conditions, probably because the gap between the bionic slat and the main wing results in favorable pressure gradient, the deployed bionic slat decreases the peak of adverse pressure gradient by increasing the chord of the bionic multi-element model, and the bionic slat wake excites transition to the boundary layer on upper surface of the main wing. This superiority may be used as reference in the design of the leading-edge slat without a cove.

APA, Harvard, Vancouver, ISO, and other styles

39

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.

Full text

Abstract:

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 shape. Under most attack angles, aerodynamic coefficients increase as the ice thickness increases. The aerodynamic load on ice-coated conductor does not increase linearly with the diameter of conductor.

APA, Harvard, Vancouver, ISO, and other styles

40

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 (June 2021): 650–59. http://dx.doi.org/10.1051/jnwpu/20213930650.

Full text

Abstract:

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 wind tunnel test data. The stall characteristics of an electric aircraft at high angle of attack are obtained by numerical simulation and analysis. According to the stall characteristics of simulation calculation, flight test is carried out to verify the reliability of numerical simulation, which provides reference for the later analysis of stall/spin test of large aspect ratio series electric aircraft at nonlinear high angle of attack.

APA, Harvard, Vancouver, ISO, and other styles

41

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.

Full text

Abstract:

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 is significant to forecast the state parameters.

APA, Harvard, Vancouver, ISO, and other styles

42

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 (October 9, 2018): 62. http://dx.doi.org/10.14419/ijet.v7i4.13.21330.

Full text

Abstract:

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 and the controller performances are studied based on their transient responses. Obtained results show that both SMCs are applicable for high angles of attack.

APA, Harvard, Vancouver, ISO, and other styles

43

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

Full text

Abstract:

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 thoseinsects filmed in free flight are presented for use in later calculations of the lift and power requirements of forward flight.

APA, Harvard, Vancouver, ISO, and other styles

44

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.

Full text

Abstract:

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 16° and Maximum lift to drag ratio (L/D) was 14 which occurred at α=3°, and the zero lift drag coefficient was 0.0342. Also the yawing moment coefficient was plotted for different side slip angles as well as rolling moment. The longitudinal stability derivatives with respect to angle of attack, speed variation (u), rate of pitch (q) and time rate of change of angle of attack were calculated using obtained CFD results. Concerning lateral stability only side slips derivatives were calculated. To validate this numerical simulation USAF Digital DATCOM is used to analyze this aircraft; a comparison between predicted results for this aircraft and Digital DATCOM indicated that this numerical simulation has high ability for predicting the aerodynamics characteristics.

APA, Harvard, Vancouver, ISO, and other styles

45

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.

Full text

Abstract:

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 models provide a low-dimensional balanced representation of the relevant unsteady fluid dynamics. In simulations, flow structures are visualized using finite-time Lyapunov exponents. A number of phenomenological trends are observed, both in the data and in the models. As the base angle of attack increases, the boundary layer begins to separate, resulting in a decreased quasi-steady lift coefficient slope and a delayed relaxation to steady state at low frequencies. This extends the low-frequency range of motions that excite unsteady effects, meaning that the quasi-steady approximation is not valid until lower frequencies than are predicted by Theodorsen’s classical inviscid model. In addition, at small angles of attack, the lift coefficient rises to the steady-state value after a step in angle, while at larger angles of attack, the lift coefficient relaxes down to the steady-state after an initially high lift state. Flow visualization indicates that this coincides with the formation and convection of vortices at the leading edge and trailing edge. As the angle of attack approaches the critical angle for vortex shedding, the poles and zeros of the model approach the imaginary axis in the complex plane, and some zeros cross into the right half plane. This has significant implications for active flow control, which are discussed. These trends are observed in both simulations and wind-tunnel data.

APA, Harvard, Vancouver, ISO, and other styles

46

Pugliese, Aldo, Zhi Gang Yang, and Qi Liang Li. "CFD Research and Investigation of 2011 P4/5 Competition Rear Wing." Applied Mechanics and Materials 275-277 (January 2013): 665–71. http://dx.doi.org/10.4028/www.scientific.net/amm.275-277.665.

Full text

Abstract:

In order to analyze the influence of the rear wing of a competition race car on the aerodynamics of the whole vehicle, computational fluid dynamics simulations have been performed. Rear wing is set by two elements, a main plate and a flap. Their relative position and the angle of attack of these elements influence the aero- performances in terms of downforce and drag generated; 12 different configurations have been generated, modifying the angle of attack and the slot gap. 3D mesh has been generated from the geometrical model of the vehicle, and air flow around the vehicle and on the rear wing has been evaluated through a CFD commercial software. It has been proved that steeper angles of attack of the mainplate and of the flap contribute to generate more downforce until a certain point; when angle of attack reaches a critical value, the downforce no longer increases and the drag still keep high values.

APA, Harvard, Vancouver, ISO, and other styles

47

WANG, JIANLEI, HUAXING LI, FENG LIU, and SHIJUN LUO. "CHARACTERISTICS OF FORE-BODY SEPARATE FLOW AT HIGH ANGLE OF ATTACK UNDER PLASMA CONTROL." Modern Physics Letters B 24, no. 13 (May 30, 2010): 1401–4. http://dx.doi.org/10.1142/s0217984910023724.

Full text

Abstract:

A pair of plasma actuators with horseshoe shape is proposed for dynamic manipulation of forebody aerodynamic load at high angles of attack. Preliminary wind tunnel pressure measurements show that asymmetric force over a conical forebody with semi-apex angle 10° can be manipulated by activating the plasma actuator mounted on one side of the cone tip. Further work is suggested.

APA, Harvard, Vancouver, ISO, and other styles

48

Li, Liang, Inderjit Chopra, Weidong Zhu, and Meilin Yu. "Performance Analysis and Optimization of a Vertical-Axis Wind Turbine with a High Tip-Speed Ratio." Energies 14, no. 4 (February 14, 2021): 996. http://dx.doi.org/10.3390/en14040996.

Full text

Abstract:

In this work, the aerodynamic performance and optimization of a vertical-axis wind turbine with a high tip-speed ratio are theoretically studied on the basis of the two-dimensional airfoil theory. By dividing the rotating plane of the airfoil into the upwind and downwind areas, the relationship among the angle of attack, azimuth, pitch angle, and tip-speed ratio is derived using the quasi-steady aerodynamic model, and aerodynamic loads on the airfoil are then obtained. By applying the polynomial approximation to functions of lift and drag coefficients with the angle of attack for symmetric and asymmetric airfoils, respectively, explicit expressions of aerodynamic loads as functions of the angle of attack are obtained. The performance of a fixed-pitch blade is studied by employing a NACA0012 model, and influences of the tip speed ratio, pitch angle, chord length, rotor radius, incoming wind speed and rotational speed on the performance of the blade are discussed. Furthermore, the optimization problem based on the dynamic-pitch method is investigated by considering the maximum value problem of the instantaneous torque as a function of the pitch angle. Dynamic-pitch laws for symmetric and asymmetric airfoils are derived.

APA, Harvard, Vancouver, ISO, and other styles

49

Atkinson, Michael, Jonathan Poggie, and José Camberos. "Control of High-Angle-of-Attack Reentry Flow with Plasma Actuators." Journal of Spacecraft and Rockets 50, no. 2 (March 2013): 337–46. http://dx.doi.org/10.2514/1.a32360.

Full text

APA, Harvard, Vancouver, ISO, and other styles

50

Gursul, Ismet. "Unsteady flow phenomena over delta wings at high angle of attack." AIAA Journal 32, no. 2 (February 1994): 225–31. http://dx.doi.org/10.2514/3.11976.

Full text

APA, Harvard, Vancouver, ISO, and other styles

We offer discounts on all premium plans for authors whose works are included in thematic literature selections. Contact us to get a unique promo code!