Multiblock analysis for shuttle orbiter reentry heating from Mach 24 to Mach 12

Gnoffo, Peter A.; Weilmuenster, K. J.; Alter, Stephen J.

doi:10.2514/3.26448

Cited by 65 publications

(22 citation statements)

References 11 publications

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“…21 Some of these solutions were redone with a refined grid and updated physical models in support of the Columbia accident investigation and Return to Flight activities. 22 The original simulations used a grid with approximately 1 million cells and a 7-species air model with an early model for surface catalysis.…”

Section: E Sts -2mentioning

confidence: 99%

Updates to Multi-Dimensional Flux Reconstruction for Hypersonic Simulations on Tetrahedral Grids

Gnoffo

2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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The quality of simulated hypersonic stagnation region heating with tetrahedral meshes is investigated by using an updated three-dimensional, upwind reconstruction algorithm for the inviscid flux vector. An earlier implementation of this algorithm provided improved symmetry characteristics on tetrahedral grids compared to conventional reconstruction methods. The original formulation however displayed quantitative differences in heating and shear that were as large as 25% compared to a benchmark, structured-grid solution. The primary cause of this discrepancy is found to be an inherent inconsistency in the formulation of the flux limiter. The inconsistency is removed by employing a GreenGauss formulation of primitive gradients at nodes to replace the previous Gram-Schmidt algorithm. Current results are now in good agreement with benchmark solutions for two challenge problems: (1) hypersonic flow over a three-dimensional cylindrical section with special attention to the uniformity of the solution in the spanwise direction and (2) hypersonic flow over a three-dimensional sphere. The tetrahedral cells used in the simulation are derived from a structured grid where cell faces are bisected across the diagonal resulting in a consistent pattern of diagonals running in a biased direction across the otherwise symmetric domain. This grid is known to accentuate problems in both shock capturing and stagnation region heating encountered with conventional, quasi-one-dimensional inviscid flux reconstruction algorithms. Therefore the test problems provide a sensitive indicator for algorithmic effects on heating. Additional simulations on a sharp, double cone and the shuttle orbiter are then presented to demonstrate the capabilities of the new algorithm on more geometrically complex flows with tetrahedral grids. These results provide the first indication that pure tetrahedral elements utilizing the updated, three-dimensional, upwind reconstruction algorithm may be used for the simulation of heating and shear in hypersonic flows in upwind, finite volume formulations.

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Section: E Sts -2mentioning

confidence: 99%

Updates to Multi-Dimensional Flux Reconstruction for Hypersonic Simulations on Tetrahedral Grids

Gnoffo

2010

48th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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“…Other applications of these codes to the orbiter vehicle have been reported, [11][12][13] and additional context of the windward laminar flow field is available in the literature.…”

Section: A Codesmentioning

confidence: 99%

Assessment of Turbulent CFD against STS-128 Hypersonic Flight Data

Wood

Kleb

Hyatt

2010

10th AIAA/ASME Joint Thermophysics and Heat Transfer Conference

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“…LAURA is a computational fluid dynamics (CFD) tool specialized for hypersonic reentry physics and chemistry. In the past, the LAURA code has been applied and validated for a range of vehicle shapes and flow conditions including the Shuttle Orbiter laminar aerothermodynamic flight data 20 , blunt planetary configurations, 21,22 and slender lifting bodies. 23 The code is a three-dimensional upwind finite-volume solver for the inviscid Euler equations, thin-layer Navier-Stokes, or full Navier-Stokes governing equations.…”

Section: Computational Simulation Of Baseline Model Surface Flowmentioning

confidence: 99%

Turbulent Supersonic/Hypersonic Heating Correlations for Open and Closed Cavities

Everhart

Greene

2009

47th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition

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Supersonic/hypersonic laminar heating correlations that were developed for damageassessment analysis of atmospheric re-entry vehicles have been modified and extended to cover fully-turbulent conditions over rectangular cavity geometries that are aligned with the local velocity. Turbulent boundary layer properties were computationally determined and used to develop the cavity geometry parametrics and to correlate experimental closed cavity heating data to yield new relationships for the floor-averaged and centerline endwall peakheating augmentation. With the form of the closed-cavity correlations established, historical data were used to develop new correlations for turbulent open-cavity heating.

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Multiblock analysis for shuttle orbiter reentry heating from Mach 24 to Mach 12

Cited by 65 publications

References 11 publications

Updates to Multi-Dimensional Flux Reconstruction for Hypersonic Simulations on Tetrahedral Grids

Updates to Multi-Dimensional Flux Reconstruction for Hypersonic Simulations on Tetrahedral Grids

Assessment of Turbulent CFD against STS-128 Hypersonic Flight Data

Turbulent Supersonic/Hypersonic Heating Correlations for Open and Closed Cavities

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