Verification of a Navier-Stokes code for solving the hypersonic blunt body problem
Computational results obtained from a Navier-Stokes code for the subsonic nose region flow on blunt bodies in supersonic flow have been evaluated for accuracy. The unsteady thin-layer form of the governing equations for a perfect gas are solved with a linearized block Alternating-Directions Implicit finite-difference solution procedure. A modification to the usual numerical scheme is required near the stagnation point to obtain satisfactory heat transfer results in this region. Sensitivity of the solutions to code input parameters is investigated. Predictions obtained from the code are presented an compared to numerical and experimental results. This study indicates that very accurate surface pressures and reasonably accurate heat transfer predictions are obtained from the code. 13 refs., 13 figs., 7 tabs.
- Research Organization:
- Sandia National Labs., Albuquerque, NM (USA)
- DOE Contract Number:
- AC04-76DP00789
- OSTI ID:
- 6648117
- Report Number(s):
- SAND-88-0917C; CONF-890151-1; ON: DE89003169
- Country of Publication:
- United States
- Language:
- English
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Related Subjects
75 CONDENSED MATTER PHYSICS
SUPERCONDUCTIVITY AND SUPERFLUIDITY
99 GENERAL AND MISCELLANEOUS
990220 -- Computers
Computerized Models
& Computer Programs-- (1987-1989)
BOUNDARY LAYERS
COMPUTER CODES
DIFFERENTIAL EQUATIONS
ENERGY TRANSFER
EQUATIONS
FLUID FLOW
HEAT FLUX
HEAT TRANSFER
HYPERSONIC FLOW
LAMINAR FLOW
LAYERS
MODIFICATIONS
N CODES
NAVIER-STOKES EQUATIONS
PARTIAL DIFFERENTIAL EQUATIONS
REYNOLDS NUMBER