Effect of endwall suction on aerodynamic performance of compressor cascade with tip clearance at a large incidence angle

Engineering

• Incidence Angle 100%
• Aerodynamic Performance 100%
• Leakage Flow 60%
• Blade Span 40%
• Loss Separation 40%
• Vortex 20%
• Flow Velocity 20%
• Flow Rate 20%
• Boundary Layer Separation 20%
• Flow Structure 20%
• Angle of Incidence 20%
• Internal Flow 20%
• Pressure Loss Coefficient 20%
• Leakage Loss 20%
• Vortex Shedding 20%
• Separation Region 20%
• Boundary Layer Suction 20%