Design and Performance Evaluation of Supercritical Airfoils for Axial Flow Compressors.

摘要

Pratt & Whitney Aircraft has developed an analytical design procedure for producing supercritical cascade airfoils satisfying practical aerodynamic and structural requirements. The purpose of this research is to demonstrate the potential for substantial efficiency improvements in compressor stages incorporating these airfoil designs. The midspan section of a fan exit stator was selected for the design application. An airfoil was designed, fabricated, and tested in a transonic cascade tunnel. Test conditions were varied over a wide range of inlet flow angles and inlet Mach numbers to determine design and off-design performance. Test point information included inlet and exit conditions and airfoil surface pressure distribution.