NASA Logo

NTRS

NTRS - NASA Technical Reports Server

Back to Results
Chemical nonequilibrium Navier-Stokes solutions for hypersonic flow over an ablating graphite nosetipThe general boundary conditions including mass and energy balances of chemically equilibrated or nonequilibrated gas adjacent to ablating surfaces have been derived. A computer procedure based on these conditions was developed and interfaced with the Navier-Stokes solver for predictions of the flow field, surface temperature, and surface ablation rates over re-entry space vehicles with ablating Thermal Protection Systems (TPS). The Navier-Stokes solver with general surface thermochemistry boundary conditions can predict more realistic solutions and provide useful information for the design of TPS. A test case with a proposed hypersonic test vehicle configuration and associated free stream conditions was developed. Solutions with various surface boundary conditions were obtained, and the effect of nonequilibrium gas as well as surface chemistry on surface heating and ablation rate were examined. The solutions of the GASP code with complete ablating surface conditions were compared with those of the ASC code. The direction of future work is also discussed.
Document ID
19930062576
Document Type
Conference Paper
Authors
Chen, Y. K. (Eloret Inst. Palo Alto, CA, United States)
Henline, W. D. (NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 16, 2013
Publication Date
July 1, 1993
Subject Category
FLUID MECHANICS AND HEAT TRANSFER
Report/Patent Number
AIAA PAPER 93-2836
Meeting Information
AIAA, Thermophysics Conference(Orlando, FL)
Funding Number(s)
CONTRACT_GRANT: NCC2-462
Distribution Limits
Public
Copyright
Other