Relevant bibliographies by topics / High angle of attack

Academic literature on the topic 'High angle of attack'

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Published: 4 June 2021
Last updated: 19 February 2022

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Journal articles on the topic "High angle of attack"

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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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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.

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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.

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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 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.
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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.

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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 (January 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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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 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.
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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 (June 3, 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 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.
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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 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.
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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.

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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) analysis techniques. The control architecture is designed to serve both for the recovery from the undesired stall condition (the stabilization controller) and to perform desired agile maneuvering (the attitude controller). The detailed modeling of the aircraft dynamics, aerodynamics, engines and thrust vectoring paddles, as well as the flight environment of the aircraft and the on-board sensors is performed. Within the control loop the human pilot model is included and the design of a fly-by-wire controller is also investigated. The performance of the designed stabilization and attitude controllers are simulated using the custom built 6 DoF aircraft flight simulation tool. As for the stabilization controller, a forced deep-stall flight condition is generated and the aircraft is recovered to stable and pilot controllable flight regimes from that undesired flight state. The performance of the attitude controller is investigated under various high angle of attack agile maneuvering conditions. Finally, the performances of the proposed controller schemes are discussed and the conclusions are made.
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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 be safely reached, although at a higher cost in drag. Variable geometry aerodynamic devices have been used in many forms of motorsport in the past offering the ability to change the relative values of downforce and drag. These have invariably been banned, generally due to safety reasons. The use of active aerodynamics is currently legal in both Formula SAE (engineering compet ition for university students to design, build and race an open-wheel race car) and production vehicles. A number of passenger car companies are beginning to incorporate active aerodynamic devices in their designs. In this research the effect of ground proximity on the lift, drag and moment coefficients of inverted, two-dimensional aerofoils was investigated. The purpose of the study was to examine the effect ground proximity on aerofoils post stall, in an effort to evaluate the use of active aerodynamics to increase the performance of a race car. The aerofoils were tested at angles of attack ranging from 0° - 135°. The tests were performed at a Reynolds number of 2.16 x 105 based on chord length. Forces were calculated via the use of pressure taps along the centreline of the aerofoils. The RMIT Industrial Wind Tunnel (IWT) was used for the testing. Normally 3m wide and 2m high, an extra contraction was installed and the section was reduced to form a width of 295mm. The wing was mounted between walls to simulate 2-D flow. The IWT was chosen as it would allow enough height to reduce blockage effect caused by the aerofoils when at high angles of incidence. The walls of the tunnel were pressure tapped to allow monitoring of the pressure gradient along the tunnel. The results show a delay in the stall of the aerofoils tested with reduced ground clearance. Two of the aerofoils tested showed a decrease in Cl with decreasing ground clearance; the third showed an increase. The Cd of the aerofoils post-stall decreased with reduced ground clearance. Decreasing ground clearance was found to reduce pitch moment variation of the aerofoils with varied angle of attack. The results were used in a simulation of a typical Formula SAE race car.
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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. This thesis uses this concept to study the effect of the differences in aerodynamic data for different aerodynamic models provided for a same aircraft which is F-18 HARV combat aircraft. The aircraft was used as a prototype for the high angles of attack technology program. However modeling an aircraft at high angles of attack requires an extensive aerodynamic data which are usually di cult to access. All aerodynamic models were collected from open literature and implemented within a nonlinear six degree of freedom aircraft model. Inspection of aerodynamic data set for these models has shown mismatches for certain aerodynamic derivatives, especially at higher angles of attack where nonlinear dynamics are known to exist. Nonlinear simulations are used to analyse three different types of flight dynamic models that use look-up-tables, arc-tangent formulation and polynomial functions to represent aerodynamic data that are suitable for high angles of attack application. To achieve this, a nonlinear six degree of freedom Simulink model was developed to accommodate these aerodynamic models separately. The trim conditions were obtained for different combinations of angles of attack and airspeed and the models were linearized in each case. Properties of the resulting state matrices such as eigenvalues and eigenvectors were studied to determine the dynamic behaviour of the aircraft at various flight conditions.
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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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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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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.
Includes bibliographical references (p. 168-170).
by Pui-Chuen Patrik Yip.
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 developed to describe the unsteady aerodynamic characteristics of the aircraft during roll oscillations. For this model, we chose to separate the aircraft into panels and model the local forces and moments. Included in this technique is the introduction of a new state variable, a separation state variable which characterizes the separation for each panel. This new variable is governed by a first order differential equation. Taylor series expansions in terms of the input variables were performed to obtain the aerodynamic coefficients of the model. These derivatives, a form of the stability derivative approach, are not constant but rather quadratic functions of the new state variable. Finally, the concept of the model was expanded to allow for the addition of longitudinal motions. Thus, pitching moments will be identified at the same time as rolling moments. The results show that the goal of modeling coupled longitudinal and lateral--directional characteristics at the same time using the same inputs is feasible.
Master of Science
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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 environment can be configured in one of three ways: l) straight uniform flow, 2) curved flow to simulated a horizontal turn, and 3) rolling flow to simulated a roll motion about the relative Velocity vector.
Ph. D.
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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. New York, NY: 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. Berlin, Heidelberg: Springer Berlin Heidelberg, 1993. http://dx.doi.org/10.1007/978-3-642-52460-8.

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High angle of attack aerodynamics: Subsonic, transonic, and supersonic flows. New York: Springer-Verlag, 1991.

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

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High Angle of Attack Aerodynamics: Subsonic, Transonic, and Supersonic Flows. New York, NY: Springer New York, 1992.

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

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Katz, Joseph. Impulsive start of a symmetric airfoil at high angle of attack. [Washington, DC: National Aeronautics and Space Administration, 1996.

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Hwang, Danny P. A numerical analysis applied to high angle of attack three-dimensional inlets. [Cleveland, Ohio: National Aeronautics and Space Administration, Lewis Research Center, 1986.

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Johnson, Dan A. Flowfield measurements in the wake of a missile at high angle of attack. Monterey, Calif: Naval Postgraduate School, 1989.

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Whitmore, Stephen A. Development of a pneumatic high-angle-of-attack flush airdata sensing (HI-FADS) system. Edwards, Calif: National Aeronautics and Space Administration, Ames Research Center, Dryden Flight Research Facility, 1991.

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Book chapters on the topic "High angle of attack"

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Rom, Josef. "Vortex Flows and the Rolled Up Vortex Wake." In High Angle of Attack Aerodynamics, 131–49. New York, NY: 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, 150–76. New York, NY: 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, 177–248. New York, NY: 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, 249–314. New York, NY: 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, 315–84. New York, NY: Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2824-0_9.

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Rom, Josef. "Introduction." In High Angle of Attack Aerodynamics, 1–7. New York, NY: 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, 8–61. New York, NY: 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, 62–77. New York, NY: 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, 78–130. New York, NY: Springer New York, 1992. http://dx.doi.org/10.1007/978-1-4612-2824-0_4.

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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, 139–53. Cham: 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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HARLOFF, GARY. "High angle of attack hypersonic aerodynamics." In 5th Applied Aerodynamics Conference. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1987. http://dx.doi.org/10.2514/6.1987-2548.

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

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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. Reston, Virigina: American Institute of Aeronautics and Astronautics, 2006. http://dx.doi.org/10.2514/6.2006-663.

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

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

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Jouannet, Christopher, and Petter Krus. "Modelling of High Angle of Attack Aerodynamic." In 25th AIAA Applied Aerodynamics Conference. Reston, Virigina: 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. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1990. http://dx.doi.org/10.2514/6.1990-219.

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

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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. Reston, Virginia: American Institute of Aeronautics and Astronautics, 2013. http://dx.doi.org/10.2514/6.2013-4980.

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Kruggel, Benjamin, Asher Sigal, Bob Whyte, and Wayne Hathaway. "High angle of attack free flight missile testing." In 37th Aerospace Sciences Meeting and Exhibit. Reston, Virigina: American Institute of Aeronautics and Astronautics, 1999. http://dx.doi.org/10.2514/6.1999-435.

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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. Fort Belvoir, VA: Defense Technical Information Center, January 1996. http://dx.doi.org/10.21236/ada436537.

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

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

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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. Fort Belvoir, VA: Defense Technical Information Center, May 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. Fort Belvoir, VA: Defense Technical Information Center, August 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. Fort Belvoir, VA: Defense Technical Information Center, October 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. Fort Belvoir, VA: Defense Technical Information Center, March 1994. http://dx.doi.org/10.21236/ada277965.

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8

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

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9

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

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10

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), May 1995. http://dx.doi.org/10.2172/61151.

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