Boundary Layer Profile Investigations Downstream of an Aero-Engine Intake Anti-Icing Air Exhaust Slot

摘要

The boundary layer profile downstream of the anti-icing air exhaust slot of a two-dimensional aeroengine inlet section was investigated by a pitot rake. Results for a range of inlet engine airflows with and without exhaust anti-icing air introduced are presented. The boundary layer is found to be turbulent as expected owing to the presence upstream in the wind tunnel of a fixed water spray grid which may be used to simulate engine operation in clouds. Injection of anti-icing air produces a sublayer downstream of the anti-icing air exhaust plane. Three methods of deriving boundary layer thickness from the experimental data were used and theoretical values determined. Experimental measurements confirm theoretical trends.