Numerical investigation of axisymmetric intake flowfield and performance for scramjet-powered ascent flight

Engineering

• Adaptive Mesh Refinement 33%
• Aerodynamics 33%
• Assuming 33%
• Axisymmetric 66%
• Boundary Layer 33%
• Centerline 33%
• Compression Efficiency 33%
• Computational Simulation 33%
• Design 33%
• Dynamic Pressure 66%
• Engines 33%
• Exit Temperature 33%
• Flow Phenomenon 33%
• High Mach Number 33%
• High Resolution 33%
• Isothermal 33%
• Mach Number 33%
• Meshes 33%
• Performance 100%
• Pressure Drag 66%
• Pressure Field 33%
• Reduced Pressure 33%
• Regular Reflection 33%
• Simulation 33%
• Temperature Field 33%
• Trajectories 66%