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

Kimiya Komurasaki, Graham V. Candler

Research output: Contribution to conferencePaperpeer-review

1 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 languageEnglish (US)
DOIs
StatePublished - 1998
Event7th Joint Thermophysics and Heat Transfer Conference, AIAA/ASME 1998 - Albuquerque, United States
Duration: Jun 15 1998Jun 18 1998

Other

Other7th Joint Thermophysics and Heat Transfer Conference, AIAA/ASME 1998
Country/TerritoryUnited States
CityAlbuquerque
Period6/15/986/18/98

Bibliographical note

Funding Information:
The authors acknowledge support from the Carnegie Mellon Climate and Energy Decision Making Center (CEDM) formed through a cooperative agreement between the NSF and CMU (SES- 0949710).We thank Jessica Barnebei for her graphics expertise. We also thank Peter Adams, Albert Presto, Jinhyok Heo, M. Granger Morgan, Nick Muller, and David Luke Oates for helpful discussions.

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

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