Laminar-to-turbulent transition prediction around the muses-c reentry capsule

Kimiya Komurasaki; Graham V. Candler

doi:10.2514/6.1998-2941

Laminar-to-turbulent transition prediction around the muses-c reentry capsule

Kimiya Komurasaki, Graham V. Candler

Aerospace Engineering and Mechanics

Research output: Contribution to conference › Paper › peer-review

2 Scopus citations

Abstract

Laminar-to-turbulent transition over an ablator heatshield of the MUSES-C reentry capsule has been analytically predicted. A two-equation turbulence model (k-ε model) was coupled with Reynolds averaged Navier-Stokes equations to reproduce the boundary flow transition. The low-Reynolds-number effect on the solid wall boundary was taken into account by modifying the Chien's correction. The results show that the turbulence induced by turbulent-gas-injection from the ablator surface was multiplied in a boundary layer, and the flow transited to turbulence. The predicted transition point Reynolds number was 3 × 10⁴ at the surface mass injection rate of 100 g/sm².

Original language	English (US)
DOIs	https://doi.org/10.2514/6.1998-2941
State	Published - 1998
Event	7th Joint Thermophysics and Heat Transfer Conference, AIAA/ASME 1998 - Albuquerque, United States Duration: Jun 15 1998 → Jun 18 1998

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Other	7th Joint Thermophysics and Heat Transfer Conference, AIAA/ASME 1998
Country/Territory	United States
City	Albuquerque
Period	6/15/98 → 6/18/98

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© 1998 The American Institute of Aeronautics and Astronautics Inc. All rights reserved.

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title = "Laminar-to-turbulent transition prediction around the muses-c reentry capsule",

abstract = "Laminar-to-turbulent transition over an ablator heatshield of the MUSES-C reentry capsule has been analytically predicted. A two-equation turbulence model (k-ε model) was coupled with Reynolds averaged Navier-Stokes equations to reproduce the boundary flow transition. The low-Reynolds-number effect on the solid wall boundary was taken into account by modifying the Chien's correction. The results show that the turbulence induced by turbulent-gas-injection from the ablator surface was multiplied in a boundary layer, and the flow transited to turbulence. The predicted transition point Reynolds number was 3 × 104 at the surface mass injection rate of 100 g/sm2.",

author = "Kimiya Komurasaki and Candler, {Graham V.}",

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year = "1998",

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AU - Komurasaki, Kimiya

AU - Candler, Graham V.

PY - 1998

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AB - Laminar-to-turbulent transition over an ablator heatshield of the MUSES-C reentry capsule has been analytically predicted. A two-equation turbulence model (k-ε model) was coupled with Reynolds averaged Navier-Stokes equations to reproduce the boundary flow transition. The low-Reynolds-number effect on the solid wall boundary was taken into account by modifying the Chien's correction. The results show that the turbulence induced by turbulent-gas-injection from the ablator surface was multiplied in a boundary layer, and the flow transited to turbulence. The predicted transition point Reynolds number was 3 × 104 at the surface mass injection rate of 100 g/sm2.

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T2 - 7th Joint Thermophysics and Heat Transfer Conference, AIAA/ASME 1998

Y2 - 15 June 1998 through 18 June 1998

ER -

Laminar-to-turbulent transition prediction around the muses-c reentry capsule

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