Modeling of Heat Transfer and Ablation of Refractory Material Due to Rocket Plume ImpingementCR Tech's Thermal Desktop-SINDA/FLUINT software was used in the thermal analysis of a flame deflector design for Launch Complex 39B at Kennedy Space Center, Florida. The analysis of the flame deflector takes into account heat transfer due to plume impingement from expected vehicles to be launched at KSC. The heat flux from the plume was computed using computational fluid dynamics provided by Ames Research Center in Moffet Field, California. The results from the CFD solutions were mapped onto a 3-D Thermal Desktop model of the flame deflector using the boundary condition mapping capabilities in Thermal Desktop. The ablation subroutine in SINDA/FLUINT was then used to model the ablation of the refractory material.
Document ID
20120015504
Acquisition Source
Kennedy Space Center
Document Type
Conference Paper
Authors
Harris, Michael F. (Sierra Lobo, Inc. Kennedy Space Center, FL, United States)
Vu, Bruce T. (NASA Kennedy Space Center Cocoa Beach, FL, United States)