Relevant bibliographies by topics / Attack angle

Contents

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

Academic literature on the topic 'Attack angle'

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

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Journal articles on the topic "Attack angle"

1

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

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Effects of a low Reynolds number flow on an airfoil with cavities of a specified shape are analyzed computationally to assess the aerodynamic performance by observing the coefficients of lift and drag with increasing angles of attacks. The Reynolds number considered for the simulation is 1×104 operating at atmospheric conditions at sea level. Indentations with a definite shape (right-angled triangle) are utilized to find the vortex effects of air in the cavity on the shear layer separation on airfoil surface to retain the flow even at higher angles of attack. The simulation is run in ANSYS Flu
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Haryanto, Ismoyo, Khoiri Rozi, Berkah Fajar TK, and Alwahidil Zuhri. "Analysis of Aerodynamics Load of a Flapping Wing by Vortex Lattice Method." International Research Journal of Innovations in Engineering and Technology 08, no. 09 (2024): 297–301. http://dx.doi.org/10.47001/irjiet/2024.809036.

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The aim of this study is to investigate the effect of changing the angle of attack and flapping angle on the aerodynamic characteristics of an unsymmetrical wing with the NACA 2412 profile. This work uses the Vortex Lattice Method. The results of this study show that increasing the flapping angle causes the pitching moment to decrease while induced drag and moment coefficient increase, meanwhile, the lift coefficient increases at positive angles of attack and then decreases at negative angles of attack. The pitching moment decreases with increasing angle of attack at positive flap angles, but
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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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Brice, Jennifer. "Angle of Attack." River Teeth: A Journal of Nonfiction Narrative 6, no. 1 (2004): 17–40. http://dx.doi.org/10.1353/rvt.2005.0003.

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

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

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This note explains why casting a loop with a positive angle of attack is advantageous in distance fly casting. Several loop shapes, one with a positive angle of attack, one with a negative angle of attack, and two symmetrical loops with zero angle of attack are studied. For each loop, we compute the vertical drag component, i.e., the “lift.” It is found that a loop with a positive angle of attack generates lift about four times larger than a symmetrical loop. Thus, loops with positive angles of attack stay “aerialized longer” which is consistent with observations made by (competition) distance
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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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Sun, Yong, and Xing Sheng Li. "Determination of Attack Angle and Tilt Angle of a Cutting Pick." Advanced Materials Research 705 (June 2013): 415–18. http://dx.doi.org/10.4028/www.scientific.net/amr.705.415.

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Mechanical excavators play an important role in mining and construction. An excavation machine cuts rocks using its cutterhead which is normally composed of a large number of cutting picks. These picks are installed on a drum with certain attack angles, tilt angles and skew angles. These angles, especially attack and tilt angles, will affect the forces acting on individual picks and the cutterhead. To ensure the reliability and productivity of the excavation machine, these angles have to be kept in their optimal values. However, in manufacturing, these three types of angles cannot be set simul
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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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Zhang, Li, Xinru Mao, and Lin Ding. "Influence of attack angle on vortex-induced vibration and energy harvesting of two cylinders in side-by-side arrangement." Advances in Mechanical Engineering 11, no. 1 (2019): 168781401882259. http://dx.doi.org/10.1177/1687814018822598.

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

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Sims, J. P. "In-flight measurement of angle of attack." Thesis, Swansea University, 1995. http://ethos.bl.uk/OrderDetails.do?uin=uk.bl.ethos.639041.

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Three possible techniques for measuring angle of attack (AOA) have been investigated with a view to establishing a low-cost method for use in light aircraft. Basically, methods using new silicon bonded pressure transducers and low cost inertial components have been compared with a standard AOA system. An Inertial Measurement Unit (IMU) and a differential pressure AOA system have been designed and constructed using the low-cost transducers and both have been installed in a twin engined general aviation aircraft along with the Teledyne AOA cone probe. A series of flight tests have been conducted
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Hoang, Ngoc T. "The hemisphere-cylinder at an angle of attack." Diss., This resource online, 1991. http://scholar.lib.vt.edu/theses/available/etd-08062007-094404/.

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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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Ganji, Farid 1967. "Control of the space shuttle angle-of-attack during reentry." Thesis, Massachusetts Institute of Technology, 2002. http://hdl.handle.net/1721.1/89340.

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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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Cohen, David E. II. "Trim Angle of Attack of Flexible Wings Using Non-Linear Aerodynamics." Diss., Virginia Tech, 1998. http://hdl.handle.net/10919/30404.

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Multidisciplinary interactions are expected to play a significant role in the design of future high-performance aircraft (Blended-Wing Body, Truss-Braced wing, High Speed Civil transport, High-Altitude Long Endurance aircraft and future military aircraft). Also, the availability of supercomputers has made it now possible to employ high-fidelity models (Computational Fluid Dynamics for fluids and detailed finite element models for structures) at the preliminary design stage. A necessary step at that stage is to calculate the wing angle-of-attack at which the wing will generate the desired lift
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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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Books on the topic "Attack angle"

1

White, Robin A. Angle of attack. Fawcett Gold Medal, 1993.

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White, Robin A. Angle of attack. Crown Publishers, 1992.

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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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United States. National Aeronautics and Space Administration., ed. High angle-of-attack aerodynamic characteristics of crescent and elliptic wings. University of California, Dept. of Mechanical Engineering, Division of Aeronautical Science and Engineering, 1989.

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Book chapters on the topic "Attack angle"

1

Seibel, Barry S. "Sculpting Angle of Attack." In Phacodynamics, 4th ed. CRC Press, 2024. http://dx.doi.org/10.1201/9781003525639-89.

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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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Conference papers on the topic "Attack angle"

1

Wu, Guangbin, Heng Li, and Junwei Lei. "Research on fixed attack angle attack angle and height flying of hypersonic aircraft." In 2015 3rd International Conference on Machinery, Materials and Information Technology Applications. Atlantis Press, 2015. http://dx.doi.org/10.2991/icmmita-15.2015.111.

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Shabana, Ahmed A., and James J. O’Shea. "Large Angle of Attack Wheel Climb." In ASME 2013 International Design Engineering Technical Conferences and Computers and Information in Engineering Conference. American Society of Mechanical Engineers, 2013. http://dx.doi.org/10.1115/detc2013-12382.

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It is shown in this paper that wheel climb can be initiated as the result of kinematic conditions that can be described using algebraic equations that do not depend explicitly on time. These algebraic kinematic conditions can lead to instantaneous wheel climb that is independent of the motion history. The analysis presented in this paper shows that if the contact is maintained at the wheel perimeter, a single kinematic constraint equation, expressed in terms of the wheel generalized coordinates, is obtained. This algebraic constraint equation clearly shows that a decrease in the lateral distan
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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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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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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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Martos, Borja, and David F. Rogers. "Low Cost Accurate Angle of Attack System." In 55th AIAA Aerospace Sciences Meeting. American Institute of Aeronautics and Astronautics, 2017. http://dx.doi.org/10.2514/6.2017-1215.

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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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Reports on the topic "Attack angle"

1

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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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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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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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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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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Stack, Cory, and Ross Wagnild. Surface Pressure Fluctuations Induced by a Hypersonic Turbulent Boundary Layer on a Sharp Cone at Angle of Attack. Office of Scientific and Technical Information (OSTI), 2024. http://dx.doi.org/10.2172/2429939.

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Bihrle, W., Barnhart Jr., Dickes B., and E. Static and Rotational Aerodynamic Data from O deg to 90 deg Angle of Attack for a Series of Basic and Altered Forebody Shapes. Defense Technical Information Center, 1989. http://dx.doi.org/10.21236/ada216582.

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