An Overset Adaptive Cartesian/Prism Grid Method for Moving Boundary Flow Problems

Wang, Z.J.; Kannan, Ravishekar

doi:10.2514/6.2005-322

Cited by 8 publications

(4 citation statements)

References 42 publications

(39 reference statements)

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“…To avoid extensive remeshing of the solution domain, overlapping mesh/grid (Chimera) schemes using generalized coordinates and transformed governing equations are commonly applied for the moving boundary problems with embedded rigid bodies 15. Here, one (embedded) grid is applied around the moving body, while another serves as the background grid.…”

Section: Introductionmentioning

confidence: 99%

A three‐dimensional hybrid meshfree‐Cartesian scheme for fluid–body interaction

Yeo

Sundar

Ang

2011

Numerical Meth Engineering

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SUMMARYA numerical method based on a hybrid meshfree-Cartesian grid is developed for solving three-dimensional fluid-solid interaction (FSI) problems involving solid bodies undergoing large motion. The body is discretized and enveloped by a cloud of meshfree nodes. The motion of the body is tracked by convecting the meshfree nodes against a background of Cartesian grid points. Spatial discretization of secondorder accuracy is accomplished by the combination of a generalized finite difference (GFD) method and conventional finite difference (FD) method, which are applied to the meshfree and Cartesian nodes, respectively. Error minimization in GFD is carried out by singular value decomposition. The discretized equations are integrated in time via a second-order fractional step projection method. A time-implicit iterative procedure is employed to compute the new/evolving position of the immersed bodies together with the dynamically coupled solution of the flow field. The present method is applied on problems of free falling spheres and tori in quiescent flow and freely rotating spheres in simple shear flow. Good agreement with published results shows the ability of the present hybrid meshfree-Cartesian grid scheme to achieve good accuracy. An application of the method to the self-induced propulsion of a deforming fish-like swimmer further demonstrates the capability and potential of the present approach for solving complex FSI problems in 3D.

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Section: Introductionmentioning

confidence: 99%

A three‐dimensional hybrid meshfree‐Cartesian scheme for fluid–body interaction

Yeo

Sundar

Ang

2011

Numerical Meth Engineering

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“…We use the concept of the marching vectors to determine the extrusion direction at any given node. This was originally used for the generation of prismatic meshes . A marching vector is a direction along which a node in the surface mesh needs to be traversed for extrusion.…”

Section: Generation Of Subject‐specific Airway Modelmentioning

confidence: 99%

Anthropometry‐based generation of personalized and population‐specific human airway models

Kannan

Chen

Przekwas

et al. 2020

Numer Methods Biomed Eng

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Understanding aerosol deposition in the human lung is of great significance in pulmonary toxicology and inhalation pharmacology. Adverse effects of inhaled environmental aerosols and pharmacological efficacy of inhaled therapeutics are dependent on aerosol properties as well as person-specific respiratory tract anatomy and physiology. Anatomical geometry and physiological function of human airways depend on age, gender, weight, fitness, health, and disease status. Tools for the generation of the population-and subject-specific virtual airway anatomical geometry based on anthropometric data and physiological vitals are invaluable in respiratory diagnostics, personalized pulmonary pharmacology, and model-based management of chronic respiratory diseases. Here we present a novel protocol and software framework for the generation of subject-specific airways based on anthropometric measurements of the subject's body, using the anatomical input, and the conventional spirometry, providing the functional (physiological) data. This model can be used for subject-specific simulations of respiration physiology, gas exchange, and aerosol inhalation and deposition. K E Y W O R D Sairway geometry, anthropometry, human lungs, inhalation aerosols, lung CT imaging, mathematical model, personalized lung model

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“…Other authors have already handled the problem of coupled rigidbody and flow dynamics (e.g., Wang and Kannan [2]). Recently, Sahu et al [3] have developed a method for generating a complete aerodynamic description of a projectile dynamics, using timeaccurate simulations and virtual "fly-out" simulations.…”

Section: Introductionmentioning

confidence: 99%

Analysis of Shroud Release Applied for High-Velocity Missiles

Dagan

Arad

2014

Journal of Spacecraft and Rockets

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A detachable missile nose was designed, tested, and implemented in a new missile. This design enables the use of lowdrag supersonic configurations for the major part of the flight, with the application of blunt seekers that are active during the end game. The configuration of the ejected shroud was designed using a novel approach, which included only a small amount of wind-tunnel experiments, coupled with an aerodynamic model produced by computational fluid dynamics. A simulation of flow dynamics, coupled with rigid-body dynamics, was developed and tested. Databases of aerodynamic forces and moments were produced using quasi-steady computations, for hinged and free flight of the shroud, at very demanding conditions of supersonic flight and large angles of attack. These databases were used by rigid-body dynamic simulations, in one-and six-degree-of-freedom modes, in order to predict the shroud's trajectories. Very good agreement with experimental data has been achieved. The present methodology enabled the analysis of hundreds of trajectories at a reasonable computation effort.Nomenclature CD 0 = zero-lift drag coefficient Cm x , Cm y , Cm z = roll, pitch, and yaw-moment coefficients C x , C y , C z = axial, side, and normal force coefficients D = missile base diameter, m F x , F y , F z = axial, side, and normal forces, N I b = moment of inertia with respect to center of gravity, N · m 2 L, M, N = roll, pitch, and yaw moment about the center of gravity, N · m L∕D = projectile length to diameter ratio l = shroud length, m m = total mass of a shroud half, kg p, q, r = angular velocity in roll, pitch, and yaw, rad∕s t ref = reference time scale, s V b = velocity vector of the shroud in a coordinates system attached to the missile, m∕s w = induced wind velocity, m∕s x, z = axial and normal coordinate, m X cg , Z cg = center of gravity location measured from the nose tip, m X NP = center of pressure location measured from the nose tip, m α, β = angle of attack and side-slip angle, deg θ = deflection angle, deg _ θ 0 = initial angular deflection velocity, rad∕s ω = angular velocity vector in a missile's attached coordinate system, rad∕s

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An Overset Adaptive Cartesian/Prism Grid Method for Moving Boundary Flow Problems

Cited by 8 publications

References 42 publications

A three‐dimensional hybrid meshfree‐Cartesian scheme for fluid–body interaction

A three‐dimensional hybrid meshfree‐Cartesian scheme for fluid–body interaction

Anthropometry‐based generation of personalized and population‐specific human airway models

Analysis of Shroud Release Applied for High-Velocity Missiles

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