Experimental lnvestigation of Laminar-Turbulent Boundary Layer Transition on Rotating Blades

Abstract

Laminar-turbulent transition on rotating blades has recently become an important design parameter for a propulsive system. For instance, a larger extent of laminar flow can reduce airfoil drag. Hence, experimental investigat ion of the transition phenomenon is inevitable for the validation of correct numeric modeling. The study presented was conducted at the rotor test facility in Göttingen on a model helicopter blade. Boundary layer transition was measured using Temperature Sensitive Paint (TSP). A second blade was instrumented with fast response pressure transducers (Kulites) providing pressure data at two radial sections.