Nozzle design optimization for axisymmetric scramjets by using surrogate-assisted evolutionary algorithms

Earth and Planetary Sciences

• Supersonic Combustion Ramjet Engine 100%
• Condition 75%
• Fuel 75%
• Shape 50%
• Parameter 50%
• Algorithms 50%
• Altitude 50%
• Thrust 50%
• Nozzle Design 50%
• Length 25%
• Value 25%
• Radii 25%
• Impact 25%
• Optimization 25%
• Balance 25%
• High Speed 25%
• Science and Technology 25%
• Geometry 25%
• Bell 25%
• Atmospheric Transport 25%
• Base Flow 25%
• Propulsion 25%
• Hypersonics 25%
• Nozzle Geometry 25%
• Design Optimization 25%
• Shape Optimization 25%

Engineering

• Fuel 75%
• Algorithm 50%
• Axisymmetric 50%
• Nozzle 50%
• Nozzle Design 50%
• High Speed 25%
• Design 25%
• Production 25%
• Optimization 25%
• Axial Force 25%
• Radius 25%
• Design Parameter 25%
• Viscous Force 25%
• Base Flow 25%
• External Surface 25%
• Analytical Approach 25%
• Design Factor 25%
• Design Optimization 25%
• Cruise Condition 25%
• Shape Optimisation 25%