Transonic Wind Tunnel Modernization for Experimental Investigation of Dynamic Stall in a Wide Range of Mach Numbers by Plasma Actuators with Combined Energy/Momentum Action.

摘要

This equipment grant supported the design and construction of a subsonic variable speed wind tunnel for the study of plasma based methods for the control of dynamic stall for helicopter rotor blades. The tunnel has a 3D positioning system and servomotor mounted below the test section connected to the model through a 6-component transducer. This control system allows complete synchronization of all events: dynamic pitching frequency and pitching angle, free stream speed, actuator s timing, and all 6-component forces measurements. The wind tunnel is fitted with large windows for extended optical access to permit various non intrusive and minimally intrusive diagnostic, including Femtosecond Laser Electronic Excitation Tagging (FLEET) to be utilized. The experimental program for plasma control requires high-voltage power sources for excitation of the air. This will be achieved with nanosecond and sub nanosecond pulse sources driving new designs of surface electrodes, as well as new dielectric and semiconducting surface structures The tunnel test section is built with dielectric walls to avoid electromagnetic interactions with the experiments.