Cartesian Adaptive Mesh Refinement for Rotorcraft Wake Resolution

Wissink, Andrew M.; Kamkar, Sean; Pulliam, Thomas H.; Sitaraman, Jayanarayanan; Sankaran, Venkateswaran

doi:10.2514/6.2010-4554

Cited by 82 publications

(40 citation statements)

References 27 publications

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“…The near-body solver is a temporally second-order and spatially secondorder-accurate solver called KCFD [6]. 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].…”

Section: Methodsmentioning

confidence: 99%

“…For the spatial solution, both central-difference schemes and upwind schemes are available to compute the convective fluxes, although only the upwind schemes were used in this work. The available upwind schemes are a thirdorder HLLE++ [7] implementation with multiple limiter options (the most commonly used is van Albada) and a fifth-order weighted essentially nonoscillatory (WENO) scheme [20,21]. SAMCart contains the same turbulence models as KCFD, and it is implemented to take advantage of the Cartesian mesh.…”

Section: B Offbody Flow Solver Samcartmentioning

confidence: 99%

“…SAMCart contains the same turbulence models as KCFD, and it is implemented to take advantage of the Cartesian mesh. The implicit time scheme used in this work is a second-order-accurate fully-implicit scheme using SSOR for the linear matrix solver [7].…”

Section: B Offbody Flow Solver Samcartmentioning

confidence: 99%

See 2 more Smart Citations

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%

Section: B Offbody Flow Solver Samcartmentioning

confidence: 99%

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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 second version of Helios, called Shasta, introduces additional capabilities such as off-body adaptive mesh refinement (AMR) for more accurate resolution of the rotor-tip vortices 7 and the ability to perform combined fuselage and rotor simulations. Advanced options such as support for flapped rotors, store separation and maneuvering flight are also being enabled.…”

Section: Introductionmentioning

confidence: 99%

“…In Section IV, we provide an overview of the validation results with the Helios-Shasta software. In particular, we focus on the testing of the off-body-AMR for flow over a NACA0015 wing, 11 the TRAM rotor in hover 7,16 and the UH-60A rotor in forward flight. 17 Validation of the other new capabilities in Shasta are still ongoing and will be summarized in a later article.…”

Section: Introductionmentioning

confidence: 99%

Overview of the Helios Version 2.0 Computational Platform for Rotorcraft Simulations

Sankaran¹,

Wissink

Datta³

et al. 2011

49th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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This article summarizes the capabilities and development of the Helios version 2.0, or Shasta, software for rotary wing simulations. Specific capabilities enabled by Shasta include off-body adaptive mesh refinement and the ability to handle multiple interacting rotorcraft components such as the fuselage, rotors, flaps and stores. In addition, a new run-mode to handle maneuvering flight has been added. Fundamental changes of the Helios interfaces have been introduced to streamline the integration of these capabilities. Various modifications have also been carried out in the underlying modules for near-body solution, off-body solution, domain connectivity, rotor fluid structure interface and comprehensive analysis to accommodate these interfaces and to enhance operational robustness and efficiency. Results are presented to demonstrate the mesh adaptation features of the software for the NACA0015 wing, TRAM rotor in hover and the UH-60A in forward flight.

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Accurate and robust adaptive mesh refinement for aerodynamic simulation with multi‐block structured curvilinear mesh

Chen

2015

Numerical Methods in Fluids

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SUMMARYA multi-block curvilinear mesh-based adaptive mesh refinement (AMR) method is developed to satisfy the competing objectives of improving accuracy and reducing cost. Body-fitted curvilinear mesh-based AMR is used to capture flow details of various length scales. A series of efforts are made to guarantee the accuracy and robustness of the AMR system. A physics-based refinement function is proposed, which is proved to be able to detect both shock wave and vortical flow. The curvilinear mesh is refined with cubic interpolation, which guarantees the aspect ratio and smoothness. Furthermore, to enable its application in complex configurations, a sub-block-based refinement strategy is developed to avoid generating invalid mesh, which is the consequence of non-smooth mesh lines or singular geometry features. A newfound problem of smaller wall distance, which negatively affects the stability and is never reported in the literature, is also discussed in detail, and an improved strategy is proposed. Together with the high-accuracy numerical scheme, a multiblock curvilinear mesh-based AMR system is developed. With a series of test cases, the current method is verified to be accurate and robust and be able to automatically capture the flow details at great cost saving compared with the global refinement.

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Cartesian Adaptive Mesh Refinement for Rotorcraft Wake Resolution

Cited by 82 publications

References 27 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

Overview of the Helios Version 2.0 Computational Platform for Rotorcraft Simulations

Accurate and robust adaptive mesh refinement for aerodynamic simulation with multi‐block structured curvilinear mesh

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