Three-dimensional numerical study on reducing hypersonic blunt body drag and aeroheating with spike-aerodisk-bleed air channel

Engineering

• Flow Field 100%
• Numerical Study 100%
• Drag Coefficient 100%
• Blunt Body 100%
• Stanton Number 100%
• Navier-Stokes Equation 50%
• Two Dimensional 50%
• Dimensional Flow Field 50%
• Axisymmetric 50%
• Major Problem 50%
• High Pressure and High Temperature 50%
• Nozzle Exit 50%
• Drag Reduction 50%
• Hypersonic Vehicles 50%
• Reynolds-Averaged Navier-Stokes 50%
• Three-Dimensional Models 50%
• Peak Value 50%
• Reattachment 50%
• Channel Structure 50%
• Air Pressure 50%
• Stagnation Point 50%
• Flow Phenomenon 50%
• Asymmetric Flow 50%