Simulation of Evaporated-Diffuse Combustion of a Single Micro Aluminum Droplet in Solid Rocket Motor

Engineering

• Rocket Engine 100%
• Aluminum Droplet 100%
• Chamber Pressure 66%
• High Gas Flow Rate 66%
• Evaporation Rate 33%
• Aluminum Powder 33%
• Combustion 33%
• Two Dimensional 33%
• Temperature Increase 33%
• Combustion Chamber 33%
• Flame Temperature 33%
• Maximum Temperature 33%
• Gas Velocity 33%
• Flow Direction 33%
• Pressure Increase 33%
• Flame Zone 33%

Material Science

• Aluminum 100%
• Gas Flow 33%
• Powder 16%
• Gas Velocity 16%