Commercial Experiment Transporter - COMET

Wessling, Francis C.; Robinson, Michael; Martinez, R.; Gallimore, Thomas; Combs, Nick

doi:10.2514/3.26522

Cited by 4 publications

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Computational Aerothermodynamic Design Issues for Hypersonic Vehicles

Gnoffo¹,

Weilmuenster²,

Hamilton³

et al. 1999

Journal of Spacecraft and Rockets

102

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A brief review of the evolutionary progress in computational aerothermodynamics is presented. The current status of computational aerothermodynamics is then discussed, with emphasis on its capabilities and limitations for contributions to the design process of hypersonic vehicles. Some topics to be highlighted include: घ1ङ aerodynamic coeaecient predictions with emphasis on high temperature gas eaeects; घ2ङ surface heating and temperature predictions for thermal protection system घTPSङ design in a high temperature, thermochemical nonequilibrium environment; घ3ङ methods for extracting and extending computational aeuid dynamic घCFDङ solutions for eaecient utilization by all members of a multidisciplinary design team; घ4ङ physical models; घ5ङ validation process and error estimation; and घ6ङ gridding and solution generation strategies. Recent experiences in the design of X-33 will be featured. Computational aerothermodynamic contributions to Mars Pathaender, METEOR, and Stardust घComet Sample returnङ will also provide context for this discussion. Some of the barriers that currently limit computational aerothermodynamics to a predominantly reactive mode in the design process will also be discussed, with the goal of providing focus for future research.

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Computational Aerothermodynamic Design Issues for Hypersonic Vehicles

Gnoffo¹,

Weilmuenster²,

Hamilton³

et al. 1999

Journal of Spacecraft and Rockets

102

View full text Add to dashboard Cite

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Aerodynamic analysis of Commercial Experiment Transporter re-entry capsule

Wood

Gnoffo

Rault

1996

Journal of Spacecraft and Rockets

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Aerothermodynamic analysis of Commercial Experiment Transporter (COMET) reentry capsule

William

Peter

Didier

1996

34th Aerospace Sciences Meeting and Exhibit

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An aerothermodynamic analysis of the Commercial Experiment Transporter (COMET) reentry capsule has been performed using the laminar thin-layer Navier-Stokes solver Langley Aerothermodynamic Upwind Relaxation Algorithm. Flowfield solutions were obtained at Mach numbers 1.5, 2, 5, 10, 15, 20, 25, and 27.5. Axisymmetric and 5, 10, and 20 degree angles of attack were considered across the Mach-number range, with the Mach 25 conditions taken to 90 degrees angle of attack and the Mach 27.5 cases taken to 60 degrees angle of attack. Detailed surface heat-transfer rates were computed at Mach 20 and 25, revealing that heating rates on the heat-shield shoulder ,can exceed t h e stagnation-point heating by 230 percent. Finiterate chemistry solutions were periormed above Mach 10, otherwise perfect gas computations were made. Drag, lift, and pitching moment coefficients are computed and details of a wake flow are presented. The effect of including the wake in the solution domain was investigated and base pressure corrections to forebody drag coefficients were numerically determined for t h e lower Mach numbers. Pitching moment comparisons are made with direct simulation Monte Carlo results in the more rarefied flow at t h e highest Mach numbers, showing agreement within two-percent. Thin-layer Navier-Stokes computations of the axial force are found to be 15 percent higher across the speed range than the empirical/Newtonian based results used during the initial trajectory analyses.

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Commercial Experiment Transporter - COMET

Cited by 4 publications

References 0 publications

Computational Aerothermodynamic Design Issues for Hypersonic Vehicles

Computational Aerothermodynamic Design Issues for Hypersonic Vehicles

Aerodynamic analysis of Commercial Experiment Transporter re-entry capsule

Aerothermodynamic analysis of Commercial Experiment Transporter (COMET) reentry capsule

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