Parameters affecting dynamic stall control by oscillatory excitation

D. Greenblatt, I. Wygnanski

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

22 Scopus citations


A parametric study was undertaken to investigate the effect of oscillatory excitation (with zero net mass-flux) on a NACA 0015 airfoil, undergoing pitch oscillations at.. rotorcraft reduced frequencies. The primary objective of the study was to maximize airfoil performance while simultaneously limiting moment excursions to typical pre-stalled conditions, The incidence angle excursions were limited to ±5°. A “wide range reduced excitation frequencies., and. amplitudes were, considered for 0.3×106≤Re≤0.9×106 with various flap deflections and excitation, locations. Both light- and deep-stall were effectively controlled by the excitation whose effects were more pronounced at higher airfoil oscillation-rates and were effectively independent of Reynolds, number. As in the previous study, oscillatory excitation was found to be far superior to steady blowing, which was even detrimental under certain conditions. Flap-shoulder excitation was found to be superior to leading-edge excitation - particularly when used in conjunction with positive flap-deflection.

Original languageEnglish (US)
Title of host publication17th Applied Aerodynamics Conference
PublisherAmerican Institute of Aeronautics and Astronautics Inc, AIAA
Number of pages14
ISBN (Print)9781563472985
StatePublished - 1999
Event17th Applied Aerodynamics Conference, 1999 - Norfolk, United States
Duration: Jun 28 1999Jul 1 1999

Publication series

Name17th Applied Aerodynamics Conference


Other17th Applied Aerodynamics Conference, 1999
Country/TerritoryUnited States

ASJC Scopus subject areas

  • General Engineering


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