PIV FLOW MEASUREMENTS ON A HIGH LIFT AIRFOIL WITH LEADING EDGE ICE

摘要

The aircraft performance decrease due to icing on a wing is an important area of concern for flight safety. A wind tunnel data base has been established for a high lift airfoil with a single flap extended, representative for a modern airliner wing. The model airfoil is equipped with a leading edge ice shape.This paper presents flow quantities measured by means of the PIV measurement technique on the airfoil upper surface over almost the full wing chord at several angles of attack in the range from pre-stall to post-stall: 0.5°, 3.5° 4.5° 5.5° 6.5° and 8.5°. The flow field was measured by three cameras synchronously, enabling to get snapshots of the full upper surface flow at once. Mean flow as well as turbulence data are presented.