Compact Fluidic Actuator Arrays for Flow Control, Phase II

The overall objective of the proposed research is to design, develop and demonstrate fluidic actuator arrays for aerodynamic separation control and drag reduction. These actuators are based on a compact design of low mass-flow fluidic oscillators that produce high frequency (1-5 kHz) sweeping jets. Preliminary experiments on separation control over a trailing edge flap on a NACA 0015 airfoil, V-22 wing section for download reduction, cavity tones and jet thrust vectoring have shown encouraging results for these actuators. Based on the results from Phase I, and the commercial interest from a leading aircraft manufacturer, we propose to conduct a systematic study of the scaling parameters of the fluidic actuator arrays in relation to the geometric and aerodynamic parameters of the wing using wind tunnel tests on a specially designed airfoil model. This will include the effects of actuator spacing, array location, pressure gradient and wing sweep on the actuator effectiveness. Failure Modes and Effects Analysis (FMEA) will be undertaken to estimate the risk of the proposed technology. A rapid inspection technique will be developed for conducting quick, in situ testing of the fluidic arrays. Projecting to the future, a synchronous array of actuators will also be developed.

This is a mature technology (TRL 7+) — the realistic path in is usually NASA's Technology Transfer Program: licensing an existing NASA patent, or a Space Act Agreement to use NASA facilities/expertise directly. NASA also runs a startup licensing program with no upfront fee for companies formed to commercialize a specific NASA technology.

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