Performance of Advanced Fan Exit Guide Vanes with a Product Derived Fan

Testing was performed on a 22 in. diameter fan model representative of a current high bypass, high speed fan in the NASA Glenn Research Center 9x1 5Foot Low Speed Wind Tunnel. Three fan exit guide vane configurations were tested with this fan for aerodynamic performance as well as acoustics, with aerodynamic performance being the scope of this paper. With the use of a simulated pylon and a bifurcated nozzle within the fan duct along with a simulated engine core complete with a core booster rotor, allowed the experiment to more closely duplicate the performance of the full scale engine. The performance data, taken with a variable fan exit nozzle in addition to flow correlation data taken with a fixed nozzle, was obtained at a tunnel Mach number of 0.04.