Numerical Investigation of Active Flow Control of Blade Synthetic Jet on Performance and Stability of Transonic Axial Compressor Rotor

Engineering

• Pressure Ratio 100%
• Suction Surface 100%
• Axial Compressors 100%
• Compressor Rotor 100%
• Casing Treatment 75%
• Stability Margin 75%
• Vortex 25%
• Rotor Blade 25%
• Design Point 25%
• Aerodynamic Performance 25%
• NASA 25%
• Peak Efficiency 25%
• Axial-Flow Compressors 25%
• Blade Tip 25%
• Main Reason 25%
• Compressor Performance 25%
• Aerodynamic Stability 25%
• Efficiency Point 25%
• Loss Separation 25%