Automatic off-body grid generation for domains of arbitrary size

Meakin, Robert L.

doi:10.2514/6.2001-2536

Cited by 56 publications

(30 citation statements)

References 3 publications

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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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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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“…The OVERFLOW-D code is the result of extensive development for a dynamic, moving-body simulation capability. [15][16][17] This capability has been demonstrated on 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 MPI (Message Passing Interface) library.…”

Section: B Computational Codesmentioning

confidence: 99%

CFD Approaches for Simulation of Wing-Body Stage Separation

Buning

Gomez

Scallion

2004

22nd Applied Aerodynamics Conference and Exhibit

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A collection of computational fluid dynamics tools and techniques are being developed and tested for application to stage separation and abort simulation for next-generation launch vehicles. In this work, 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 a belly-to-belly wing-body configuration. Steady cases show excellent agreement between Navier-Stokes results, Cartesian grid Euler solutions, and wind tunnel data at Mach 3. Good agreement has been obtained between Navier-Stokes, Euler, and wind tunnel results at Mach 6. An analysis of a dynamic separation at Mach 3 demonstrates that unsteady aerodynamic effects are not important for this scenario. Results provide an illustration of the relative applicability of Euler and Navier-Stokes methods to these types of problems.

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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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Automatic off-body grid generation for domains of arbitrary size

Cited by 56 publications

References 3 publications

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

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

CFD Approaches for Simulation of Wing-Body Stage Separation

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

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