Open-loop and closed-loop trailing-edge separation control on a natural laminar flow airfoil

Rohit Gupta, Phillip J. Ansell

Research output: Chapter in Book/Report/Conference proceedingConference contribution

Abstract

Active Unsteady Flow Control experiments were performed on a Natural Laminar Flow, NLF 0414 airfoil at Rec = 1.0 × 106. The goal of this study was to control boundary-layer separation across the trailing-edge region of the airfoil in off-design conditions. Both open-loop and closed-loop control approaches were used. Active control of separation was achieved using a series of blowing slots at the x/c = 0.75 location. Open loop control parameters were varied across a parametric range of jet amplitudes, actuation frequencies and duty cycles and performance measurements were acquired to identify the effectiveness of these actuation schemes. PIV measurements were acquired across a horizontal plane near the trailing edge region of the model to understand the effects of actuation on flow separation and the vortex dynamics associated with unsteady actuation. A closed loop controller was developed to vary the actuation parameters in-situ using sensory feedback from the unsteady surface pressure measurements and adaptive modal decomposition methods. This closed-loop system was able to automatically control the extent of separation such that a desired value of Cl was obtained.

Original languageEnglish (US)
Title of host publication54th AIAA Aerospace Sciences Meeting
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
ISBN (Print)9781624103933
DOIs
StatePublished - 2016
Event54th AIAA Aerospace Sciences Meeting, 2016 - San Diego, United States
Duration: Jan 4 2016Jan 8 2016

Publication series

Name54th AIAA Aerospace Sciences Meeting
Volume0

Other

Other54th AIAA Aerospace Sciences Meeting, 2016
CountryUnited States
CitySan Diego
Period1/4/161/8/16

ASJC Scopus subject areas

  • Aerospace Engineering

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