A data-driven polynomial chaos method for uncertainty quantification of a subsonic compressor cascade with stagger angle errors

Engineering

• Aerodynamic Performance 66%
• Boundary Layer Thickness 33%
• Bubble Size 33%
• Calculation Accuracy 33%
• Combined Method 33%
• Compressor Blade 33%
• Computational Fluid Dynamics 33%
• Design Condition 66%
• Engineering Application 33%
• Exit Flow 33%
• Flow State 33%
• Input Parameter 33%
• Input Uncertainty 33%
• Leading Edge 33%
• Loss Coefficient 33%
• Measurement Data 33%
• Sampled Data 100%
• Separation Bubble 33%
• Uncertainty Quantification 100%