Object X-rays for cutting holes in composite overset structured grids

Meakin, Robert L.

doi:10.2514/6.2001-2537

Cited by 140 publications

(66 citation statements)

References 6 publications

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“…Cases where the grid points lie inside the solid body defined by other grids are called hole points, and solutions are not performed on these points. The location of hole points is done via the X-ray method [21].…”

Section: Chimera Overset Gridsmentioning

confidence: 99%

The benefits of planar circular mouths on suction feeding performance

Skorczewski

Cheer

Wainwright

2012

J. R. Soc. Interface.

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Suction feeding is the most common form of prey capture across aquatic feeding vertebrates and many adaptations that enhance efficiency and performance are expected. Many suction feeders have mechanisms that allow the mouth to form a planar and near-circular opening that is believed to have beneficial hydrodynamic effects. We explore the effects of the flattened and circular mouth opening through computational fluid dynamics simulations that allow comparisons with other mouth profiles. Compared to mouths with lateral notches, we find that the planar mouth opening results in higher flow rates into the mouth and a region of highest flow that is positioned at the centre of the mouth aperture. Planar mouths provide not only for better total fluid flow rates through the mouth but also through the centre of the mouth near where suction feeders position their prey. Circular mouths are shown to provide the quickest capture times for spherical and elliptical prey because they expose the prey item to a large region of high flow. Planar and circular mouths result in higher flow velocities with peak flow located at the centre of the mouth opening and they maximize the capacity of the suction feeders to exert hydrodynamic forces on the prey.

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Section: Chimera Overset Gridsmentioning

confidence: 99%

The benefits of planar circular mouths on suction feeding performance

Skorczewski

Cheer

Wainwright

2012

J. R. Soc. Interface.

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“…The OVERFLOW-D code is the result of extensive development for a dynamic, moving-body simulation capability. 19,20,21 This capability has been demonstrated on a number of applications, including store separation, rotorcraft, and missile problems. OVERFLOW-D includes 6-degree-offreedom dynamic motion, automatic background grid generation, fast hole-cutting and grid connectivity, and parallel computation via the MPI (Message Passing Interface) library.…”

Section: Methodsmentioning

confidence: 99%

Experimental Stage Separation Tool Development in NASA Langley's Aerothermodynamics Laboratory

Murphy

Scallion

2005

AIAA Atmospheric Flight Mechanics Conference and Exhibit

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As part of the research effort at NASA in support of the stage separation and ascent aerothermodynamics research program, proximity testing of a generic bimese wing-body configuration was conducted in NASA Langley's Aerothermodynamics Laboratory in the 20-Inch Mach 6 Air Tunnel. The objective of this work is the development of experimental tools and testing methodologies to apply to hypersonic stage separation problems for future multi-stage launch vehicle systems. Aerodynamic force and moment proximity data were generated at a nominal Mach number of 6 over a small range of angles of attack. The generic bimese configuration was tested in a belly-to-belly and back-to-belly orientation at 86 relative proximity locations. Over 800 aerodynamic proximity data points were taken to serve as a database for code validation. Longitudinal aerodynamic data generated in this test program show very good agreement with viscous computational predictions. Thus a framework has been established to study separation problems in the hypersonic regime using coordinated experimental and computational tools.

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“…The OVERFLOW-D code is the result of extensive development for a dynamic, moving-body simulation capability. 20,21,22 This capability has been demonstrated on a number of applications, including store separation, rotorcraft, and missile problems. OVERFLOW-D includes 6-degree-of-freedom dynamic motion, automatic background grid generation, fast hole-cutting and grid connectivity, and parallel computation via the Message Passing Interface (MPI) library.…”

Section: Computational Codesmentioning

confidence: 99%

Overview of Transonic to Hypersonic Stage Separation Tool Development for Multi-Stage-To-Orbit Concepts

Murphy

Buning

Pamadi

et al. 2004

24th AIAA Aerodynamic Measurement Technology and Ground Testing Conference

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An overview of research efforts at NASA in support of the stage separation and ascent aerothermodynamics research program is presented. The objective of this work is to develop a synergistic suite of experimental, computational, and engineering tools and methods to apply to vehicle separation across the transonic to hypersonic speed regimes. Proximity testing of a generic bimese wing-body configuration is on-going in the transonic (Mach numbers 0.6, 1.05, and 1.1), supersonic (Mach numbers 2.3, 3.0, and 4.5) and hypersonic (Mach numbers 6 and 10) speed regimes in four wind tunnel facilities at the NASA Langley Research Center. An overset grid, Navier-Stokes flow solver has been enhanced and demonstrated on a matrix of proximity cases and on a dynamic separation simulation of the bimese configuration. Steady-state predictions with this solver were in excellent agreement with wind tunnel data at Mach 3 as were predictions via a Cartesian-grid Euler solver. Experimental and computational data have been used to evaluate multi-body enhancements to the widely-used Aerodynamic Preliminary Analysis System, an engineering methodology, and to develop a new software package, "SepSim," for the simulation and visualization of vehicle motions in a stage separation scenario. Web-based software will be used for archiving information generated from this research program into a database accessible to the user community. Thus, a framework has been established to study stage separation problems using coordinated experimental, computational, and engineering tools.

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Object X-rays for cutting holes in composite overset structured grids

Cited by 140 publications

References 6 publications

The benefits of planar circular mouths on suction feeding performance

The benefits of planar circular mouths on suction feeding performance

Experimental Stage Separation Tool Development in NASA Langley's Aerothermodynamics Laboratory

Overview of Transonic to Hypersonic Stage Separation Tool Development for Multi-Stage-To-Orbit Concepts

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