Multidisciplinary simulation of a regeneratively cooled thrust chamber of liquid rocket engine: Turbulent combustion and nozzle flow

Engineering

• Flow in Nozzles 100%
• Axisymmetric 50%
• Turbulent Boundary Layer 50%
• Chamber Wall 50%
• Characteristic Velocity 50%
• Cooling Channel 50%
• Specific Impulse 50%
• Flamelets 50%
• Fossil Fuel 50%
• Heat Convection 50%
• Hydraulics 50%
• Conjugate Convective Heat Transfer 50%