A powered, 15% scale 4 bladed rotor system was tested in conjuction with a pressure-instrumented fuselage in the 14x22 foot Subsonic Tunnel for five(5) weeks during the spring of 1995. The model included powered tail fan,and velocity data were aquired near the fan using 3-D Laser Veloci- metry as well as the new technique 3-D Doppler Global Velocimetry. The fuselage surface was instrumented with over 200 pressure transducers, force,and moment data on the rotor system and the fuselage were acquired through two(2) seperate six component strain gage balances.
