Fundamental study of supersonic combustion in pure air flow with use of shock tunnel

Physics

• Region 100%
• Combustion 100%
• Shock Tunnels 100%
• Supersonic Combustion 100%
• Pressure 50%
• Hydrogen 50%
• Information 50%
• Air 50%
• Supersonics 50%
• Penetration 50%
• Fuel 50%
• Shock Wave 50%
• Air Flow 50%
• Stagnation Pressure 50%
• Stagnation Temperature 50%

Engineering

• Obtains 50%
• Freestream 50%
• Fuel 50%
• Nozzle 50%
• Reflected Shock 50%
• Air Flow 50%
• Circular Hole 50%
• Heated Air 50%
• Schlieren Method 50%
• Stagnation Pressure 50%
• Gas Injection 50%
• Stagnation Temperature 50%
• Test Experiment 50%
• Gas Reservoir 50%