Automated Off-Body Cartesian Mesh Adaption for Rotorcraft Simulations

Kamkar, Sean; Jameson, Antony; Wissink, Andrew M.; Sankaran, Venkateswaran

doi:10.2514/6.2011-1269

Cited by 24 publications

(12 citation statements)

References 24 publications

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“…17 The Cartesian solver also uses the Method of Lines to decouple the temporal and spatial solutions. For the spatial solution, the structured, homogeneous mesh SAMCart employs blurs the distinction between finite-difference and finite-volume techniques, as viewed by the underlying flux-calculation algorithms.…”

Section: Off-body Flow Solver Samcartmentioning

confidence: 99%

Numerical Simulation of the F-16XL at Full-Scale Flight Test Conditions Using a Near-Body Off-Body CFD Approach

Morton

McDaniel

2015

33rd AIAA Applied Aerodynamics Conference

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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, is available for a wide range of flight conditions, allowing direct comparison between computational fluid dynamics and fullscale 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 HPCMP CREATE TM -AV Kestrel fixed-wing simulation tool to the F-16XL configuration at high-angle-of-attack flight conditions. Kestrel couples a near-body, spatially 2 nd -order solver with an off-body, spatially 3 rd -or 5 th -order solver to achieve a very high-resolution computation of the aerodynamic features of the flow-field. Adaptive mesh refinement (AMR) is also performed in the off-body domain as the solution progresses to maintain the vortical structures away from the body. The resulting simulation data is compared to flight test data, and found to be in very good agreement for this flight condition.

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Section: Off-body Flow Solver Samcartmentioning

confidence: 99%

Numerical Simulation of the F-16XL at Full-Scale Flight Test Conditions Using a Near-Body Off-Body CFD Approach

Morton

McDaniel

2015

33rd AIAA Applied Aerodynamics Conference

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show abstract

“…Today's industrial maturity of numerical simulation methods opens the way for a better understanding of the local flow physics in the vicinity of rotor blade tips. The most accurate simulations of isolated rotors use Adaptative Mesh Refinement (AMR) [6] , and high-order schemes to reduce numerical diffusion in the wake, as well as high-order turbulence closures or correction for vortical flows (e.g. [7,8]) to avoid unrealistic turbulent diffusion in vortex cores.…”

Section: Introductionmentioning

confidence: 99%

“…! , the near and far wakes of the considered blade and the wake of the other blade(s) 6. induced velocity at the location of the considered blade, computed using the comprehensive rotor code HOST.…”

mentioning

confidence: 99%

Numerical investigation of the vortex roll-up from a helicopter blade tip using a novel fixed-wing adaptation method

et al. 2017

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This contribution relates to the simulation of the flow around the tip of a helicopter rotor blade in hovering flight conditions. We here propose a new methodology of framework adaptation, using a comprehensive rotor code and highfidelity numerical simulations. We construct an equivalent fixed-wing configuration from a rotating blade, in which centrifugal and Coriolis forces are neglected. The effect of this approximation on the solution is analysed. The method is validated by a detailed comparison with wind tunnel data from the literature, concerning aerodynamic properties and tip vortex roll-up. This validation also includes variations of the pitch angle and rotational speed, up to transonic tip velocities. Compared to previously published methods of framework adaptation, the new hybrid method is found to reproduce more accurately the flow around a rotating blade tip.

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“…It should be noted that AMR of the offbody mesh system used a related criteria called the scaled Q criterion [23] set to one. The scaled Q criterion (SQ) is defined to be…”

Section: A Three-dimensional Flowfield Imagesmentioning

confidence: 99%

“…The SAMCart offbody solver is made up of three distinct parts: the Cartesian solver containing the governing equations and numerical solver, the automatic Cartesian mesh generator and load balancer structured adaptive mesh refinement application infrastructure (SAMRAI) [18], and the adaptive mesh refinement code GAMR [19]. The Cartesian solver also uses the method of lines to decouple the temporal and spatial solutions.…”

Section: B Offbody Flow Solver Samcartmentioning

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.

show abstract

Automated Off-Body Cartesian Mesh Adaption for Rotorcraft Simulations

Cited by 24 publications

References 24 publications

Numerical Simulation of the F-16XL at Full-Scale Flight Test Conditions Using a Near-Body Off-Body CFD Approach

Numerical Simulation of the F-16XL at Full-Scale Flight Test Conditions Using a Near-Body Off-Body CFD Approach

Numerical investigation of the vortex roll-up from a helicopter blade tip using a novel fixed-wing adaptation method

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

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