Near-Stall Modelling of a Pitching Airfoil at High Incidence, Mach Number and Reduced Frequency

The prediction accuracy of aeroelastic stability in fans and compressors depends crucially on the underlying aerodynamic predictions. prevalent approach field solves unsteady Reynolds-averaged Navier—Stokes equations presence blade vibration. Given unsteady, three-dimensional often separated nature flow regimes interest, confidence URANS methods is questionable. This paper uses simple test case a pitching symmetric aerofoil with sharp leading edge to illustrate challenges modelling. It compares coupled numerical simulations against time-resolved experimental measurements. response its dependency tip-clearance time-averaged incidence angle are analyzed. results indicate that differences aerodynamics between different approaches close stall can have significant impact local damping. Furthermore, for chosen there strong correspondence quasi-steady behaviour which weakens, but still present, towards stall.