基于改进的k-ω-γ转捩模式预测高超声速飞行器气动特性

Engineering

• Aerodynamic Characteristic 100%
• Angle-of-Attack 16%
• Boundary Layer Transition 100%
• Drag Coefficient 33%
• Engineering Application 16%
• Flow Simulation 16%
• Greater Effect 16%
• Hypersonic Vehicles 100%
• Laminar Flows 16%
• Lift Coefficient 16%
• Mach Number 16%
• Pitching Moment Coefficient 16%
• Pressure Ratio 16%
• Propulsion System 16%
• Reynolds' Number 16%

Physics

• Aerodynamic Characteristic 100%
• Angle of Attack 16%
• Boundary Layer Transition 100%
• Hypersonic Vehicle 100%
• Jet Flow 16%
• Mach Number 16%
• Pitching Moment 16%
• Reynolds Number 16%