Pages that link to "Item:Q1643695"
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The following pages link to Application of a partitioned field approach to transient aerothermal problems in rocket nozzles (Q1643695):
Displaying 5 items.
- A numerical simulation on the infrared radiation of hot exhausting nozzles with a coupled flow and heat transfer model (Q2393382) (← links)
- A monolithic computational approach to thermo-structure interaction (Q2952344) (← links)
- Numerical Simulation of Heat Loads in a Cryogenic H2/O2 Rocket Combustion Chamber (Q3061482) (← links)
- (Q3795467) (← links)
- Partitioned procedures for the transient solution of coupled aeroelastic problems. II: Energy transfer analysis and three-dimensional applications (Q5935690) (← links)