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)|
|State||Published - 1998|
|Event||7th Joint Thermophysics and Heat Transfer Conference, AIAA/ASME 1998 - Albuquerque, United States|
Duration: Jun 15 1998 → Jun 18 1998
|Other||7th Joint Thermophysics and Heat Transfer Conference, AIAA/ASME 1998|
|Period||6/15/98 → 6/18/98|
Bibliographical noteFunding 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.
© 1998 The American Institute of Aeronautics and Astronautics Inc. All rights reserved.