Parallel domain connectivity algorithm for unsteady flow computations using overlapping and adaptive grids

Sitaraman, Jayanarayanan; Floros, Matthew; Wissink, Andrew M.; Potsdam, Mark

doi:10.1016/j.jcp.2010.03.008

Cited by 138 publications

(55 citation statements)

References 24 publications

(23 reference statements)

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“…The offbody Cartesian solver is a temporally second-order and spatially third-or fifth-order upwind difference or fifth-order central difference solver called SAMCart [7,8]. The solutions are coupled spatially using an overset mesh methodology and a domain connectivity component called parallel unsteady domain information toolkit [9]. Both the near-body and offbody solvers use an implicit second-order time integration through the commonly used backward difference formula, and they are coupled using a subiteration approach, resulting in an overall temporal order of accuracy of two.…”

Section: Methodsmentioning

confidence: 99%

F-16XL Simulations at Flight Conditions Using Hybrid Near-Body/Offbody Computational Fluid Dynamics

Morton

McDaniel

2017

Journal of Aircraft

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The F-16XL flight vehicle has been used extensively to study the aerodynamics of medium-to high-angle-of-attack flight. Flight-test data, including surface pressures, are available for a wide range of flight conditions, allowing direct comparison between computational fluid dynamics and full-scale flight data. The most recent comprehensive study, made possible by NASA, was conducted by NATO Task Group AVT-113 and had participants from many different countries. One of the conclusions of the study was that unsteady flow simulations with high-resolution turbulence treatment was necessary to compare well with the high-angle-of-attack flight-test data. The current work applies the high performance computing CREATE™-Air Vehicles Kestrel fixed-wing simulation tool to the F-16XL configuration at high-angle-of-attack flight conditions. Kestrel couples a near-body spatially second-order solver with an offbody, spatially third-or fifth-order solver to achieve a very high-resolution computation of the aerodynamic features of the flowfield. Adaptive mesh refinement is also performed in the offbody domain as the solution progresses to maintain the vortical structures away from the body. The resulting simulation data are compared to flight-test data, and they are found to be in very good agreement for this flight condition.

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Section: Methodsmentioning

confidence: 99%

F-16XL Simulations at Flight Conditions Using Hybrid Near-Body/Offbody Computational Fluid Dynamics

Morton

McDaniel

2017

Journal of Aircraft

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“…The related previous investigations are extensive and various methods are developed, such as explicit and implicit methods for hole cutting, 10-12 inverse map, 13 neighbor-to-neighbor (N2N) 14 and alternating digital tree (ADT) searching algorithm 15 for donor cell searching. Based on these previous studies, a more adaptable scheme is designed and applied in the present work to meet the requirements for tilt rotor aircraft calculation as described in detail as follows.…”

Section: Grid Systemmentioning

confidence: 99%

Numerical study on flow fields and aerodynamics of tilt rotor aircraft in conversion mode based on embedded grid and actuator model

Zhang

Liang

Yang

2015

Chinese Journal of Aeronautics

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A method combining rotor actuator disk model and embedded grid technique is presented in this paper, aimed at predicting the flow fields and aerodynamic characteristics of tilt rotor aircraft in conversion mode more efficiently and effectively. In this method, rotor's influence is considered in terms of the momentum it impacts to the fluid around it; transformation matrixes among different coordinate systems are deduced to extend actuator method's utility to conversion mode flow fields' calculation. Meanwhile, an embedded grid system is designed, in which grids generated around fuselage and actuator disk are regarded as background grid and minor grid respectively, and a new method is presented for 'donor searching' and 'hole cutting' during grid assembling. Based on the above methods, flow fields of tilt rotor aircraft in conversion mode are simulated, with threedimensional Navier-Stokes equations discretized by a second-order upwind finite-volume scheme and an implicit lower-upper symmetric Gauss-Seidel (LU-SGS) time-stepping scheme. Numerical results demonstrate that the proposed CFD method is very effective in simulating the conversion mode flow fields of tilt rotor aircraft. ª 2015 Production and hosting by Elsevier Ltd. on behalf of CSAA & BUAA.

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“…Instead, for every time step, they re-establish the inter-grid connectivity. The techniques enabling simulation of objects in an arbitrary rigid body relative motion with a set of overlapping each other grid blocks are referred to as the overset or the Chimera approaches [7,8,9,10,11,12]. In a large class of problems the direction of relative motion of the grid blocks is restricted and known apriori.…”

Section: Introductionmentioning

confidence: 99%

Enhancing performance and scalability of data transfer across sliding grid interfaces for time-accurate unsteady simulations of multistage turbomachinery flows

2015

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Parallel domain connectivity algorithm for unsteady flow computations using overlapping and adaptive grids

Cited by 138 publications

References 24 publications

F-16XL Simulations at Flight Conditions Using Hybrid Near-Body/Offbody Computational Fluid Dynamics

F-16XL Simulations at Flight Conditions Using Hybrid Near-Body/Offbody Computational Fluid Dynamics

Numerical study on flow fields and aerodynamics of tilt rotor aircraft in conversion mode based on embedded grid and actuator model

Enhancing performance and scalability of data transfer across sliding grid interfaces for time-accurate unsteady simulations of multistage turbomachinery flows

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