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Relevant bibliographies by topics / Unsteady flow (Aerodynamics) Equations of state. Aerodynamics, Supersonic

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Academic literature on the topic 'Unsteady flow (Aerodynamics) Equations of state. Aerodynamics, Supersonic'

Author: Grafiati

Published: 4 June 2021

Last updated: 8 February 2022

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Journal articles on the topic "Unsteady flow (Aerodynamics) Equations of state. Aerodynamics, Supersonic"

1

Fazilati, Jamshid, Vahid Khalafi, and Hossein Shahverdi. "Three-dimensional aero-thermo-elasticity analysis of functionally graded cylindrical shell panels." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering 233, no. 5 (2018): 1715–27. http://dx.doi.org/10.1177/0954410018763861.

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In the present paper, the aero-thermo-elastic behavior of a finite (three-dimensional) cylindrical curved panel geometry made from functionally graded material under high supersonic airflow is investigated. A generalized differential quadrature formulation is adopted while a steady-state through-the-thickness thermal field is also assumed. The geometry curvature and structural nonlinearity effects are included based on von Karman–Donnell strain–displacement relations. The nonlinear piston theory of third order is utilized in order to predict the unsteady aerodynamics loads induced from surroun

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2

Lei, Wei Dong, Guo Cai Hu, and Quan Liu. "State-Space Model and Simulation for Dynamic Stall." Advanced Materials Research 989-994 (July 2014): 2258–63. http://dx.doi.org/10.4028/www.scientific.net/amr.989-994.2258.

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Because of the complexity of the progress of dynamic stall, the characteristic of dynamic stall of airfoil is always the difficulty of aerodynamics. A time-domain model has been formulated to represent the unsteady lift and pitching moment characteristics of a two-dimensional airfoil undergoing attached-flow conditions in a compressible flow and dynamic stall. The model is given as a set of first order differential state equations. The Beddoes-Leishman model was presented through modeling the effects of attached flow, separated flow and dynamic stall in the paper. A modified method is presente

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3

Chughtai, F. A., J. Masud, and S. Akhtar. "Unsteady aerodynamics computation and investigation of magnus effect on computed trajectory of spinning projectile from subsonic to supersonic speeds." Aeronautical Journal 123, no. 1264 (2019): 863–89. http://dx.doi.org/10.1017/aer.2019.32.

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AbstractThis paper describes the extensive numerical investigation carried out on a 203-mm spin-stabilised projectile to study the effects of Magnus force at high angles of attack on the stability and flight-trajectory parameters, for further validation and incorporation in a 6-DOF trajectory solver for flight-stability analysis. Magnus force typically influences the course of flight by causing the projectile to drift from its intended path in addition to generation of inbuilt dynamic instabilities in pitch and yaw orientation and is a function of AoA and spin rate. This study is a consolidati

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4

Freskos, G., and O. Penanhoat. "Numerical Simulation of the Flow Field Around Supersonic Air-Intakes." Journal of Engineering for Gas Turbines and Power 116, no. 1 (1994): 116–23. http://dx.doi.org/10.1115/1.2906780.

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The demand for efficiency in today’s and in future civil aircraft is such that experimental studies alone do not suffice to optimize aircraft aerodynamics. In this context, much effort has been spent in the past decade to develop numerical methods capable of reproducing the phenomena that occur in the engine flow field. This paper presents some studies in Computational Fluid Dynamics related to supersonic inlets. Two approaches are considered. First, there is a need for a code capable of calculating in a cost-efficient way the entire flow field around a two-dimensional or three-dimensional inl

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5

de Andrade, Donizeti, and David A. Peters. "Coupling of a State-Space Inflow to Nonlinear Blade Equations and Extraction of Generalized Aerodynamic Force Mode Shapes." Applied Mechanics Reviews 46, no. 11S (1993): S295—S304. http://dx.doi.org/10.1115/1.3122648.

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The aeroelastic stability of helicopter rotors in hovering flight has been investigated by a set of generalized dynamic wake equations and hybrid equations of motion for an elastic blade cantilevered in bending and having a torsional root spring to model pitch-link flexibility. The generalized dynamic wake model employed is based on an induced flow distribution expanded in a set of harmonic and radial shape functions, including undetermined time dependent coefficients as aerodynamic states. The flow is described by a system of first-order, ordinary differential equations in time, for which the

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6

ABBAS, LAITH K., Q. CHEN, P. MARZOCCA, K. O'DONNELL, and D. VALENTINE. "AEROELASTIC BEHAVIOR OF LIFTING SURFACES WITH FREE-PLAY, AND AERODYNAMIC STIFFNESS AND DAMPING NONLINEARITIES." International Journal of Bifurcation and Chaos 18, no. 04 (2008): 1101–26. http://dx.doi.org/10.1142/s0218127408020860.

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Aeroelastic instabilities are dangerous phenomena, where aerodynamic load interacting with the inertia and elastic structural loads can induce catastrophic failures. In this paper the effects of aerodynamic nonlinearities as well as coupled plunging/pitching structural concentrated cubic type and freeplay nonlinearities in the dynamic of a two-dimensional double-wedge airfoil immersed in supersonic/hypersonic flow has been examined. The unsteady nonlinear aerodynamic force and moment on the airfoil are evaluated using the Piston Theory Aerodynamics modified to take into account the effect of t

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7

Berci, Marco, and Rauno Cavallaro. "A Hybrid Reduced-Order Model for the Aeroelastic Analysis of Flexible Subsonic Wings—A Parametric Assessment." Aerospace 5, no. 3 (2018): 76. http://dx.doi.org/10.3390/aerospace5030076.

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A hybrid reduced-order model for the aeroelastic analysis of flexible subsonic wings with arbitrary planform is presented within a generalised quasi-analytical formulation, where a slender beam is considered as the linear structural dynamics model. A modified strip theory is proposed for modelling the unsteady aerodynamics of the wing in incompressible flow, where thin aerofoil theory is corrected by a higher-fidelity model in order to account for three-dimensional effects on both distribution and deficiency of the sectional air load. Given a unit angle of attack, approximate expressions for t

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8

Sayma, A. I., C. Bre´ard, M. Vahdati, and M. Imregun. "Aeroelasticity Analysis of Air-Riding Seals for Aero-Engine Applications." Journal of Tribology 124, no. 3 (2002): 607–16. http://dx.doi.org/10.1115/1.1467086.

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This paper presents the results of a feasibility study on air-riding seal aeroelasticity for large-diameter aero-engines. A literature survey of previous seal studies revealed a significant amount of experimental work but numerical modeling using CFD techniques was relatively scarce. Indeed, most existing theoretical studies either deal with the structural behavior, or use simplified flow modeling. The aeroelasticity stability of a simplified air-riding seal geometry, devised for this particular feasibility study, was analyzed in three dimensions for typical engine operating conditions. Both t

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9

Sina, S. A., T. Farsadi, and H. Haddadpour. "Aeroelastic Stability and Response of Composite Swept Wings in Subsonic Flow Using Indicial Aerodynamics." Journal of Vibration and Acoustics 135, no. 5 (2013). http://dx.doi.org/10.1115/1.4023992.

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In this study, the aeroelastic stability and response of an aircraft swept composite wing in subsonic compressible flow are investigated. The composite wing was modeled as an anisotropic thin-walled composite beam with the circumferentially asymmetric stiffness structural configuration to establish proper coupling between bending and torsion. Also, the structural model consists of a number of nonclassical effects, such as transverse shear, material anisotropy, warping inhibition, nonuniform torsional model, and rotary inertia. The finite state form of the unsteady aerodynamic loads have been m

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10

Yadav, Rajesh, and Aslesha Bodavula. "Numerical investigation of the effect of triangular cavity on the unsteady aerodynamics of NACA 0012 at a low Reynolds number." Proceedings of the Institution of Mechanical Engineers, Part G: Journal of Aerospace Engineering, June 17, 2021, 095441002110270. http://dx.doi.org/10.1177/09544100211027042.

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Time accurate numerical simulations were conducted to investigate the effect of triangular cavities on the unsteady aerodynamic characteristics of NACA 0012 airfoil at a Reynolds number of 50,000. Right-angled triangular cavities are placed at 10%, 25% and 50% chord location on the suction and have depths of 0.025c and 0.05c, measured normal to the surface of the airfoil. The second-order accurate solution to the RANS equations is obtained using a pressure-based finite volume solver with a four-equation transition turbulence model, γ–Re θt, to model the effect of turbulence. The two-dimensiona

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Dissertations / Theses on the topic "Unsteady flow (Aerodynamics) Equations of state. Aerodynamics, Supersonic"

1

Bundy, Christopher. "Effects of unsteady flow and real gas equations of state on high pressure ram accelerator operation /." Thesis, Connect to this title online; UW restricted, 2001. http://hdl.handle.net/1773/10008.

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Books on the topic "Unsteady flow (Aerodynamics) Equations of state. Aerodynamics, Supersonic"

1

Yates, E. Carson. Integral-equation methods in steady and unsteady subsonic, transonic and supersonic aerodynamics for interdisciplinary design. National Aeronautics and Space Administration, Langley Research Center, 1990.

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2

Center, Langley Research, ed. Integral-equation methods in steady and unsteady subsonic, transonic and supersonic aerodynamics for interdisciplinary design. National Aeronautics and Space Administration, Langley Research Center, 1990.

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3

Center, Langley Research, ed. Integral-equation methods in steady and unsteady subsonic, transonic and supersonic aerodynamics for interdisciplinary design. National Aeronautics and Space Administration, Langley Research Center, 1990.

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4

Integral-equation methods in steady and unsteady subsonic, transonic and supersonic aerodynamics for interdisciplinary design. National Aeronautics and Space Administration, Langley Research Center, 1990.

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5

W, Swafford Timothy, Reddy T. S. R, and Lewis Research Center, eds. Euler flow predictions for an oscillating cascade using a high resolution wave-split scheme. National Aeronautics and Space Administration, Lewis Research Center, 1991.

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Conference papers on the topic "Unsteady flow (Aerodynamics) Equations of state. Aerodynamics, Supersonic"

1

Tokuyama, Yuki, Ken-ichi Funazaki, Hiromasa Kato, Noriyuki Shimiya, Mitsuru Shimagaki, and Masaharu Uchiumi. "Computational Analysis of Unsteady Flow in a Partial Admission Supersonic Turbine Stage." In ASME Turbo Expo 2014: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2014. http://dx.doi.org/10.1115/gt2014-26071.

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Turbines used in upper stage engine for a rocket are sometimes designed as a supersonic turbine with partial admission. This study deals with numerical investigation of supersonic partial admission turbine in order to understand influences on the unsteady flow pattern, turbine losses and aerodynamic forces on rotor blades due to partial admission configuration. Two-dimensional CFD analysis is conducted using “Numerical Turbine” code. Its governing equation is URANS (Unsteady Reynolds Averaged Navier-Stokes Simulation) and fourth-order MUSCL TVD scheme is used for advection scheme. The unsteady

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2

Gerolymos, G. A. "Periodicity, Superposition, and 3D Effects in Supersonic Compressor Flutter Aerodynamics." In ASME 1988 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1988. http://dx.doi.org/10.1115/88-gt-136.

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In this work, a family of methods, both blade-to-blade surface and 3D, based on the numerical integration of the unsteady Euler equations, are used in studying various aspects of the unsteady aerodynamics of vibrating compressor cascades, in the supersonic flutter region. Most aerodynamic methods assume a traveling wave assembly mode of structural vibration, and suppose that the associated chorochronical periodicity is also encountered in the flowfield. This hypothesis has been tested by simulating the flow in a full annular cascade and has been verified in all the cases we have studied. When

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3

Freskos, G., and O. Penanhoat. "Numerical Simulation of the Flow Field Around Supersonic Air-Intakes." In ASME 1992 International Gas Turbine and Aeroengine Congress and Exposition. American Society of Mechanical Engineers, 1992. http://dx.doi.org/10.1115/92-gt-206.

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The demand for efficiency in today’s and in future civil aircraft is such that experimental studies alone do not suffice to optimize aircraft aerodynamics. In this context, much effort has been spent in the past decade to develop numerical methods capable of reproducing the phenomena that occur in the engine flow field. This paper presents some studies in Computational Fluid Dynamics related to supersonic inlets. Two approaches are considered. First, there is a need for code capable of calculating in a cost-efficient way the entire flow field around a 2D or 3D inlet, e.g. to perform parametric

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4

Radulescu, Victorita. "Solution to Optimize the Airfoils Shapes Placed Into a Supersonic Viscous Flow." In ASME 2018 International Mechanical Engineering Congress and Exposition. American Society of Mechanical Engineers, 2018. http://dx.doi.org/10.1115/imece2018-86781.

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To improve the airfoils performances placed in supersonic flow is proposed a method of optimization for their shapes, in order to minimize the effect of the landing vortices. The theoretical modeling starts with the Navier-Stokes equations applied for thin layers, supplemented with additional conditions related to the profile shape. For a proper estimation of efficiency and responses at different flow regime’s conditions, were considered four aerodynamics airfoils, with different shapes and functioning characteristics. Two of them are special shapes of supersonic profiles and the other two ded

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5

Li, Jing, and Robert E. Kielb. "Effects of Blade Count Ratio on Aerodynamic Forcing and Mode Excitability." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-43304.

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The effects of blade count ratio (BCR) on both the steady and unsteady blade loading and the sensitivity of generalized force to a change in mode shape (mode excitability) are studied numerically on two 2D configurations: a subsonic research compressor stage and a turbine stage with supersonic exit. Using the Harmonic Balance method, only a single passage is modeled to represent the actual blade count in a row at a high level of computational efficiency. BCR variation is achieved by scaling the downstream airfoils with a fixed chord-to-pitch ratio, thus preserving the steady-state aerodynamics

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