Relevant bibliographies by topics / High angle of attack

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  1. Journal articles
  2. Dissertations / Theses
  3. Books
  4. Book chapters
  5. Conference papers
  6. Reports

Academic literature on the topic 'High angle of attack'

Author: Grafiati
Published: 4 June 2021
Last updated: 25 July 2025

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Journal articles on the topic "High angle of attack"

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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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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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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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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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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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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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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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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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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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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Dissertations / Theses on the topic "High angle of attack"

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Atesoglu, Ozgur Mustafa. "High Angle Of Attack Maneuvering And Stabilization Control Of Aircraft." Phd thesis, METU, 2007. http://etd.lib.metu.edu.tr/upload/12608575/index.pdf.

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In this study, the implementation of modern control techniques, that can be used both for the stable recovery of the aircraft from the undesired high angle of attack flight state (stall) and the agile maneuvering of the aircraft in various air combat or defense missions, are performed. In order to accomplish this task, the thrust vectoring control (TVC) actuation is blended with the conventional aerodynamic controls. The controller design is based on the nonlinear dynamic inversion (NDI) control methodologies and the stability and robustness analyses are done by using robust performance (RP) a
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Walter, Daniel James, and Daniel james walter@gmail com. "Study of aerofoils at high angle of attack in ground effect." RMIT University. Aerospace, Mechanical and Manufacturing Engineering, 2007. http://adt.lib.rmit.edu.au/adt/public/adt-VIT20080110.145138.

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Aerodynamic devices, such as wings, are used in higher levels of motorsport (Formula-1 etc.) to increase the contact force between the road and tyres (i.e. to generate downforce). This in turn increases the performance envelope of the race car. However the extra downforce increases aerodynamic drag which (apart from when braking) is generally detrimental to lap-times. The drag acts to slow the vehicle, and hinders the effect of available drive power and reduces fuel economy. Wings, in automotive use, are not constrained by the same parameters as aircraft, and thus higher angles of attack can b
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Petterson, Kristian. "The aerodynamics of slender aircraft forebodies at high angle of attack." Thesis, Cranfield University, 2001. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.392234.

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Mohmad, Rouyan Nurhana. "Model simulation suitable for an aircraft at high angle of attack." Thesis, Cranfield University, 2016. http://dspace.lib.cranfield.ac.uk/handle/1826/9722.

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Simulation of a dynamic system is known to be sensitive to various factors and one of them could be the precision of model parameters. While the sensitivity of flight dynamic simulation to small changes in aerodynamic coefficients is typically not studied, the simulation of aircraft required to operate in nonlinear flight regimes usually at high angles of attack can be very sensitive to such small differences. Determining the significance and impact of the differences in aerodynamic characteristics is critical for understanding the flight dynamics and designing suitable flight control laws. Th
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Stucke, Russell Andrew. "High Angle-of-Attack Yaw Control Using Strakes on Blunt-Nose Bodies." University of Toledo / OhioLINK, 2006. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1167777201.

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Yip, Pui-Chuen Patrick. "A comparison of control design options for high angle-of-attack flights." Thesis, Massachusetts Institute of Technology, 1991. http://hdl.handle.net/1721.1/13431.

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Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Aeronautics and Astronautics, 1991, and Thesis (M.S.)--Massachusetts Institute of Technology, Dept. of Electrical Engineering and Computer Science.<br>Includes bibliographical references (p. 168-170).<br>by Pui-Chuen Patrik Yip.<br>M.S.
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Stagg, Gregory A. "An Aerodynamic Model for Use in the High Angle of Attack Regime." Thesis, Virginia Tech, 1998. http://hdl.handle.net/10919/35596.

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Harmonic oscillatory tests for a fighter aircraft using the Dynamic Plunge--Pitch--Roll model mount at Virginia Tech Stability Wind Tunnel are described. Corresponding data reduction methods are developed on the basis of multirate digital signal processing. Since the model is sting mounted, the frequencies associated with sting vibration are included in balance readings thus a linear filter must be used to extract out the aerodynamic responses. To achieve this, a Finite Impulse Response (FIR) is designed using the Remez exchange algorithm. Based on the reduced data, a state--space model is
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Ko, Joon Soo. "Analysis of the dynamic stability derivatives for high angle of attack aircraft." Diss., Virginia Polytechnic Institute and State University, 1985. http://hdl.handle.net/10919/52300.

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Modern, high performance aircraft are required to be able to fly and be controlled over a wide variety of flight conditions. In order to predict the aircraft behavior and control requirements over the entire flight regime it is necessary to have a proper aerodynamic model. Flight conditions at high angles of attack lead to separated flows making the aerodynamic model more difficult to obtain. In this research wind tunnel experiments are performed on an F-5 air-craft model at high angles of attack, with small oscillations about the body oriented roll axis. In addition the free stream environmen
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Ravi, R. "High Angle of Attack Forebody Flow Physics and Design Emphasizing Directional Stability." Diss., This resource online, 1997. http://scholar.lib.vt.edu/theses/available/etd-01252008-163458/.

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Sirangu, Vijaya. "AERODYNAMIC CONTROL OF SLENDER BODIES AT HIGH ANGLES OF ATTACK." University of Toledo / OhioLINK, 2010. http://rave.ohiolink.edu/etdc/view?acc_num=toledo1271365316.

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Books on the topic "High angle of attack"

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Rom, Josef. High Angle of Attack Aerodynamics. Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2824-0.

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Kawamura, R., and Y. Aihara, eds. Fluid Dynamics of High Angle of Attack. Springer Berlin Heidelberg, 1993. http://dx.doi.org/10.1007/978-3-642-52460-8.

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Center, Langley Research, ed. A High angle of attack inviscid shuttle orbiter computation. National Aeronautics and Space Administration, Langley Research Center, 1992.

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Ostroff, Aaron J. Longitudinal-control design approach for high-angle-of-attack aircraft. Langley Research Center, 1993.

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Ostroff, Aaron J. Longitudinal-control design approach for high-angle-of-attack aircraft. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., ed. Actuator and aerodynamic modeling for high-angle-of-attack aeroservoelasticity. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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S, Proffitt Melissa, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Program., eds. Longitudinal-control design approach for high-angle-of-attack aircraft. National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1993.

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8

A, Regenie Victoria, and Dryden Flight Research Facility, eds. The F-18 High Alpha Research Vehicle: A high-angle-of-attack testbed aircraft. National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, 1992.

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Victoria, Regenie, and Dryden Flight Research Facility, eds. The F-18 High Alpha Research Vehicle: A high-angle-of-attack testbed aircraft. National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, 1992.

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Victoria, Regenie, and Dryden Flight Research Facility, eds. The F-18 High Alpha Research Vehicle: A high-angle-of-attack testbed aircraft. National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, 1992.

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Book chapters on the topic "High angle of attack"

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Rom, Josef. "Introduction." In High Angle of Attack Aerodynamics. Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2824-0_1.

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Rom, Josef. "Description of Flows at High Angles of Attack." In High Angle of Attack Aerodynamics. Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2824-0_2.

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Rom, Josef. "The Topology of Separating and Reattaching Vortical Flows." In High Angle of Attack Aerodynamics. Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2824-0_3.

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Rom, Josef. "Linear Aerodynamics of Wings and Bodies." In High Angle of Attack Aerodynamics. Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2824-0_4.

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Rom, Josef. "Vortex Flows and the Rolled Up Vortex Wake." In High Angle of Attack Aerodynamics. Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2824-0_5.

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Rom, Josef. "Nonlinear Aerodynamics of Wings and Bodies at High Angles of Attack." In High Angle of Attack Aerodynamics. Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2824-0_6.

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Rom, Josef. "The Nonlinear Panel Methods for Aircraft and Missile Configurations at High Angles of Attack." In High Angle of Attack Aerodynamics. Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2824-0_7.

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Rom, Josef. "Solutions of the Euler Equations for Flows over Configurations at High Angles of Attack." In High Angle of Attack Aerodynamics. Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2824-0_8.

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Rom, Josef. "Solutions of the Navier-Stokes Equations for Flows over Configurations at High Angles of Attack." In High Angle of Attack Aerodynamics. Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2824-0_9.

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Kok, J., M. Fuchs, and C. Mockett. "Delta Wing at High Angle of Attack." In Notes on Numerical Fluid Mechanics and Multidisciplinary Design. Springer International Publishing, 2017. http://dx.doi.org/10.1007/978-3-319-52995-0_7.

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Conference papers on the topic "High angle of attack"

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Wang, Baobao, Bin Xin, Shuaishuai Wan, and Shoufeng Wang. "A Tracking and Forecasting Method of High-Angle Dive Attack Target." In 2024 43rd Chinese Control Conference (CCC). IEEE, 2024. http://dx.doi.org/10.23919/ccc63176.2024.10662156.

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HARLOFF, GARY. "High angle of attack hypersonic aerodynamics." In 5th Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2548.

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Granasy, Peter. "Thrust vectoring at high angle of attack." In Aircraft Engineering, Technology, and Operations Congress. American Institute of Aeronautics and Astronautics, 1995. http://dx.doi.org/10.2514/6.1995-3923.

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Lin, Tony, Moon Kim, Linda Sproul, Franky Choi, and Tumkur Shivananda. "High Angle of Attack Aerodynamics and Aerothermodynamics." In 44th AIAA Aerospace Sciences Meeting and Exhibit. American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-663.

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Jouannet, Christopher, and Petter Krus. "Modelling of High Angle of Attack Aerodynamic." In 25th AIAA Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 2007. http://dx.doi.org/10.2514/6.2007-4295.

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KREKELER, JR., GREGORY, DAVID WILSON, and DAVID RILEY. "High angle of attack flying qualities criteria." In 28th Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-219.

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Simon, James, and William Blake. "Missile Datcom - High angle of attack capabilities." In 24th Atmospheric Flight Mechanics Conference. American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-4258.

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CHAMBERS, J. "High-angle-of-attack aerodynamics - Lessons learned." In 4th Applied Aerodynamics Conference. American Institute of Aeronautics and Astronautics, 1986. http://dx.doi.org/10.2514/6.1986-1774.

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Baer, Steven. "F-35A High Angle of Attack Testing." In AIAA Atmospheric Flight Mechanics Conference. American Institute of Aeronautics and Astronautics, 2014. http://dx.doi.org/10.2514/6.2014-2057.

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Dias, Joaquim N., and Fabio Almeida. "High Angle of Attack Model Identification Without Air Flow Angle Measurements." In AIAA Atmospheric Flight Mechanics (AFM) Conference. American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-4980.

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Reports on the topic "High angle of attack"

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Menon, P. K., and M. Yousefpor. Design of Nonlinear Autopilots for High Angle of Attack Missiles. Defense Technical Information Center, 1996. http://dx.doi.org/10.21236/ada436537.

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Sternberg, C. A., Ricardo Traven, and James Lackey. Navy and the HARV: High Angle of Attack Tactical Utility Issues. Defense Technical Information Center, 1994. http://dx.doi.org/10.21236/ada284128.

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Sahu, Jubaraj, Karen Heavey, and Surya Dinavahi. Application of CFD to High Angle of Attack Missile Flow Fields. Defense Technical Information Center, 2000. http://dx.doi.org/10.21236/ada384925.

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AIR FORCE TEST PILOT SCHOOL EDWARDS AFB CA. Volume II. Flying Qualities Flight Testing Phase. Chapter 10: High Angle of Attack. Defense Technical Information Center, 1991. http://dx.doi.org/10.21236/ada319981.

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SCHNEIDER, Steven P., and Steven H. Collicott. Laminar-Turbulent Transition in High-Speed Compressible Boundary Layers with Curvature: Non-Zero Angle of Attack Experiments. Defense Technical Information Center, 1997. http://dx.doi.org/10.21236/ada329733.

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Orkwis, Paul D. A Study of Asymmetric Vortex Shedding Behind Missiles at High Angle of Attack Using Dynamic Solution Adaptive Meshes. Defense Technical Information Center, 1995. http://dx.doi.org/10.21236/ada304583.

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McInville, Roy M., and Frank G. Moore. A New Method for Calculating Wing Along Aerodynamics to Angle of Attack 180 deg. Defense Technical Information Center, 1994. http://dx.doi.org/10.21236/ada277965.

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Stupakov, Gennady V. High-Frequency Impedance of Small-Angle Collimators. Office of Scientific and Technical Information (OSTI), 2002. http://dx.doi.org/10.2172/800015.

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Stupakov, Gennady. Impedance of Small-Angle Collimators in High-Frequency Limit. Office of Scientific and Technical Information (OSTI), 2001. http://dx.doi.org/10.2172/784937.

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Shipley, Derek E., Mark S. Miller, Michael C. Robinson, Marvin W. Luttges, and David A. Simms. Techniques for the Determination of Local Dynamic Pressure and Angle of Attack on a Horizontal Axis Wind Turbine. Office of Scientific and Technical Information (OSTI), 1995. http://dx.doi.org/10.2172/61151.

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