Method for Extracting the Boundary Layer Loss in Any Position of the Cascade and Its Application

Total pressure loss coefficient is related to the boundary-layer energy thickness, boundarylayer edge velocity and density by theoretical derivation which can be used to calculate the boundary layer flow loss in any position of the cascade. The reliability of the formula is examined by processing the calculation results of MISES and CFX. Then the loss formula is used to analyse the development of the suction and pressure surface boundary layer loss caused by viscosity and the its variation with the inlet flow angle in a typical transonic compressor cascade. The analysis results reveal the main source of the boundary layer loss in the transonic cascade which provide the basic theory support for the optimization of the airfoil shape.