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Letteratura scientifica selezionata sul tema "Attack angle"

Autore: Grafiati

Pubblicato: 4 giugno 2021

Ultima modifica: 2 febbraio 2022

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Articoli di riviste sul tema "Attack angle"

Yeston, J. "Angle of Attack". Science 337, n. 6096 (16 agosto 2012): 779. http://dx.doi.org/10.1126/science.337.6096.779-b.

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Brice, Jennifer. "Angle of Attack". River Teeth: A Journal of Nonfiction Narrative 6, n. 1 (2004): 17–40. http://dx.doi.org/10.1353/rvt.2005.0003.

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Jiang, Hai Bo, Yan Ru Li e Zhong Qing Cheng. "Relations of Lift and Drag Coefficients of Flow around Flat Plate". Applied Mechanics and Materials 518 (febbraio 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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Gollomp, B. "The angle of attack". IEEE Instrumentation & Measurement Magazine 4, n. 1 (marzo 2001): 57–58. http://dx.doi.org/10.1109/5289.911179.

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Gatti-Bono, Caroline, e N. C. Perkins. "Effect of Loop Shape on the Drag-Induced Lift of Fly Line". Journal of Applied Mechanics 71, n. 5 (1 settembre 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 fly casters.

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Sun, Yong, e Xing Sheng Li. "Determination of Attack Angle and Tilt Angle of a Cutting Pick". Advanced Materials Research 705 (giugno 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 simultaneously. They have to be respectively set one after another. As a result, the angle which is set previously will be changed by the angles which are determined after it. Understanding the relationship between the values of the final angle and the designed angle is important for optimizing drum and pick design. This paper develops a formula for quantitatively analyzing this relationship, with the research scope limited to attack angle and tilt angle only as the first stage of the study.

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Tang, Hui, Yulong Lei, Xingzhong Li e Yao Fu. "Numerical investigation of the aerodynamic characteristics and attitude stability of a bio-inspired corrugated airfoil for MAV or UAV applications". Energies 12, n. 20 (22 ottobre 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. 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.

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Xu, Yihang, Shaosong Chen e Hang Zhou. "Analysis of the Magnus Moment Aerodynamic Characteristics of Rotating Missiles at High Altitudes". International Journal of Aerospace Engineering 2021 (12 aprile 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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Zhang, Li, Xinru Mao e 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, n. 1 (gennaio 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 leads to a phase difference between the wake patterns of the two cylinders. Hydrokinetic energy can be obviously harvested when Re > 4000. Compared with the larger attack angle case, the two side-by-side cylinders with smaller attack angle have better performance on energy conversion. The maximum energy conversion efficiency of 21.7% is achieved. The optimum region for energy conversion is 5000 ≤ Re ≤ 7000 and 0°≤ α ≤ 30°.

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Popowski, Stanisław, e Witold Dąbrowski. "MEASUREMENT AND ESTIMATION OF THE ANGLE OF ATTACK AND THE ANGLE OF SIDESLIP". Aviation 19, n. 1 (30 marzo 2015): 19–24. http://dx.doi.org/10.3846/16487788.2015.1015293.

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The paper presents issues concerning the estimation of the angle of attack and the angle of sideslip on a flying object board. Angle of attack and sideslip estimation methods which are based on measurements of linear velocity components of an object with the Earth’s coordinates and on attitude angles of the object are presented. Both of these measurements originate from the inertial navigation system, and velocity measurement is obtained from the satellite navigation system. The idea of applying inertial and satellite navigation for the estimation of attack and sideslip angles is presented. Practical comparison of these estimation methods has been conducted based on logged parameters of a flight onboard a Mewa aircraft. Development proposals for these methods are presented as well.

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Tesi sul tema "Attack angle"

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 to analyze and compare the three AOA sensors and the results have shown that the low-cost differential pressure sensor system provided data as good as the more expensive commercial unit for approximately one-tenth of its cost. The IMU system required high accuracy in the acceleration channels and though this precluded the use of low-cost accelerometers, the low-cost rate and attitude sensors coupled with the high accuracy accelerometers did provide adequate AOA data. The final results demonstrated that the differential pressure AOA was accurate to within ±0.50° and the low-cost IMU (with high accuracy acceleration calculated AOA) was accurate to within ±1.50°.

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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) 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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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, e 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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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 for the specific flight maneuver. Determination of this angle, a simple affair when the wing is rigid and the flow regime linear, becomes difficult when the wing is flexible and the flow regime non-linear. To solve this inherently nonlinear problem, a Newton's method type algorithm is developed to simultaneously calculate the deflection and the angle of attack. The present algorithm requires the sensitivity of the aerodynamic pressure with respect to each of the generalized displacement coordinates needed to represent the structural displacement. This sensitivity data is easy to determine analytically when the flow regime is linear. The present algorithm uses a finite difference method to obtain these sensitivities and thus requires only the pressure data and the surface geometry from the aerodynamic model. This makes it ideally suited for nonlinear aerodynamics for which it is difficult to obtain the sensitivity analytically. The present algorithm requires the CFD code to be run for each of the generalized coordinates. Therefore, to reduce the number of generalized coordinates considerably, we employ the modal superposition approach to represent the structural displacements. Results available for the Aeroelastic Research Wing (ARW) are used to evaluate the performance of the modal superposition approach. Calculations are made at a fixed angle of attack and the results are compared to both the experimental results obtained at NASA Langley Research Center, and computational results obtained by the researchers at NASA Ames Research Center. Two CFD codes are used to demonstrate the modular nature of this research. Similarly, two separate Finite Element codes are used to generate the structural data, demonstrating that the algorithm is not dependent on using specific codes. The developed algorithm is tested for a wing, used for in-house aeroelasticity research at Boeing (previously McDonnell Douglas) Long Beach. The trim angle of attack is calculated for a range of desired lift values. In addition to the Newton's method algorithm, a non derivative method (NDM) based on fixed point iteration, typical of fixed angle of attack calculations in aeroelasticity, is employed. The NDM, which has been extended to be able to calculate trim angle of attack, is used for one of the cases. The Newton's method calculation converges in fewer iterations, but requires more CPU time than the NDM method. The NDM, however, results in a slightly different value of the trim angle of attack. It should be noted that NDM will converge in a larger number of iterations as the dynamic pressure increases. For one value of the desired lift, both viscous and inviscid results were generated. The use of the inviscid flow model while not resulting in a markedly different value for the trim angle of attack, does result in a noticeable difference both in the wing deflection and the span loading when compared to the viscous results. A crude (coarse-grain) parallel methodology was used in some of the calculations in this research. Although the codes were not parallelized, the use of modal superposition made it possible to compute the sensitivity terms on different processors of an IBM SP/2. This resulted in a decrease in wall clock time for these calculations. However, even with the parallel methodology, the CPU times involved may be prohibitive (approximately 5 days per Newton iteration) to any practical application of this method for wing analysis and design. Future work must concentrate on reducing these CPU times. Two possibilities: (i) The use of alternative basis vectors to further reduce the number of basis vectors used to represent the structural displacement, and (ii) The use of more efficient methods for obtaining the flow field sensitivities. The former will reduce the number of CFD analyses required the latter the CPU time per CFD analysis. NOTE: (03/2007) An updated copy of this ETD was added after there were patron reports of problems with the file.
Ph. D.

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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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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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Abstract (sommario):

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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Più fonti

Libri sul tema "Attack angle"

White, Robin A. Angle of attack. New York: Crown Publishers, 1992.

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

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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., e Y. Aihara, a cura di. 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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Angle of attack: Harrison Storms and the race to the moon. New York: W.W. Norton, 1992.

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Capitoli di libri sul tema "Attack angle"

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 e 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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Atti di convegni sul tema "Attack angle"

Wu, Guangbin, Heng Li e 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. Paris, France: Atlantis Press, 2015. http://dx.doi.org/10.2991/icmmita-15.2015.111.

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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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Shabana, Ahmed A., e 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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Abstract (sommario):

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 distance between the center of mass of the wheel and the rail, which can be the result of application of a lateral force, leads to an instantaneous wheel climb in the case of a constant angle of attack. It is shown that the ratio between the lateral and vertical reaction forces at the contact point is governed by a well-defined algebraic equation, and such a ratio does not depend on the applied forces. This ratio is given by dy/(dz sin2 α), where dy and dz are, respectively, the lateral and vertical distances of the wheel center from the contact point, and α is the angle of attack. In order to develop the governing dynamic equations, the kinematic constraint equations are used to derive a velocity transformation matrix that defines the relationship between the wheel velocities and the derivatives of the degrees of freedom. This velocity transformation matrix is used to obtain the independent wheel equations of motion which are solved numerically to determine the wheel motion in response to different lateral and friction forces. The results obtained show that wheel climb can be initiated with small lateral force, and an increase in the lateral force is not necessary for climb initiation. In order to shed light on the L/V ratio commonly used in wheel climb derailment criteria, the relationship between the external lateral force acting on the wheel and the reaction lateral force at the contact point is developed in this investigation. It is also shown that in the case of a tangent track and zero roll angle; the wheel longitudinal motion is completely decoupled from the vertical and yaw displacements. Therefore, the use of the distance to climb in tangent track wheel climb criteria needs to be reexamined.

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Dias, Joaquim N., e 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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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 e 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, e 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, e 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 e 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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Rapporti di organizzazioni sul tema "Attack angle"

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

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

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Sternberg, C. A., Ricardo Traven e James Lackey. Navy and the HARV: High Angle of Attack Tactical Utility Issues. Fort Belvoir, VA: Defense Technical Information Center, marzo 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, maggio 1991. http://dx.doi.org/10.21236/ada319981.

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

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SCHNEIDER, Steven P., e 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, agosto 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, ottobre 1995. http://dx.doi.org/10.21236/ada304583.

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Shipley, Derek E., Mark S. Miller, Michael C. Robinson, Marvin W. Luttges e 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), maggio 1995. http://dx.doi.org/10.2172/61151.

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

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Stetson, Kenneth F. Hypersonic Laminar Boundary Layer Transition. Part 1. Nosetip Bluntness Effects on Cone Frustum Transition. Part 2. Mach 6 Experiments of Transition on a Cone at Angle of Attack. Fort Belvoir, VA: Defense Technical Information Center, dicembre 1986. http://dx.doi.org/10.21236/ada178877.

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