Numerical prediction of compressible heat flow with complex wall temperature in supersonic rocket nozzles
Wall heat transfer coefficients and static wall pressures are determined over wide ranges of stagnation pressures and stagnation temperatures under large pressure gradients in a cooled convergent-divergent nozzle. The effects of specific heat ratio, turbulent Prandtl number and wall temperature valu...
| Main Authors: | , |
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| Format: | Article |
| Language: | English |
| Published: |
VINCA Institute of Nuclear Sciences
2018-01-01
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| Series: | Thermal Science |
| Subjects: | |
| Online Access: | http://www.doiserbia.nb.rs/img/doi/0354-9836/2018/0354-98361600270B.pdf |