Flow Field Investigations on a Wing Installed Counter Rotation Ultra-High-Bypass Fan Engine Simulator in the Low Speed Wind Tunnel DNW-LST.

摘要

For a better understanding of jet interferences from wing mounted turbofan engines and for improved CFD modelling more detailed flow field studies and reliable test data are required. With this objective, within the framework of the DLR-NLR co-operation, flow field investigations have been carried out in the Low Speed wind Tunnel LST 3x2.25 sq. m. of the DNW (German Dutch Wind tunnels) on a twin-jet transport aircraft half model (ALVAST). The half model was tested in cruise configuration (clean wing without flaps) without and with a wing mounted engine simulator. Two types of engine simulators were used: a Through Flow Nacelle (TFN) and a turbo-powered Counter Rotating Ultra-high bypass Fan (CRUF). All tests have been carried out at wind tunnel speed V(sub 0)=60 m/s (Mach number M(sub 0)=0.18). The flow fields behind the wing and engine simulators (TFN and CRUF) were investigated using a rake equipped with total pressure probes and a rake equipped with directional probes. In this way time-averaged flow field planes perpendicular to the tunnel flow were obtained. Non-intrusive flow field measurements were carried out using the Particle Image Velocimetry (PIV) technique.