Dynamic stall control by oscillatory forcing

D. Greenblatt; I. Wygnanski

doi:10.2514/6.1998-676

Dynamic stall control by oscillatory forcing

D. Greenblatt, I. Wygnanski

Research output: Contribution to conference › Paper › peer-review

25 Scopus citations

Abstract

A parametric study was undertaken to investigate the effect of oscillatory forcing (with zero net mass-flux) on an airfoil undergoing pitch oscillations at rotorcraft reduced frequencies. The primary objective of the study was to maximize the airfoil performance while simultaneously limiting moment excursions to typical pre-stalled conditions. The incidence angle excursions were limited to ±5° and a wide range reduced forcing frequencies and amplitudes were considered for Re<0.3×10⁶ with various flap deflections and forcing locations. Significant increases in maximum lift and reductions in form drag were attained while simultaneously containing the moment excursions. Oscillatory forcing was found to be far superior to steady blowing and flap-shoulder forcing was found to be superior to leading-edge forcing.

Original language	English (US)
DOIs	https://doi.org/10.2514/6.1998-676
State	Published - 1998
Externally published	Yes
Event	36th AIAA Aerospace Sciences Meeting and Exhibit, 1998 - Reno, United States Duration: Jan 12 1998 → Jan 15 1998

Other

Other	36th AIAA Aerospace Sciences Meeting and Exhibit, 1998
Country/Territory	United States
City	Reno
Period	1/12/98 → 1/15/98

ASJC Scopus subject areas

General Engineering
Space and Planetary Science

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10.2514/6.1998-676

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title = "Dynamic stall control by oscillatory forcing",

abstract = "A parametric study was undertaken to investigate the effect of oscillatory forcing (with zero net mass-flux) on an airfoil undergoing pitch oscillations at rotorcraft reduced frequencies. The primary objective of the study was to maximize the airfoil performance while simultaneously limiting moment excursions to typical pre-stalled conditions. The incidence angle excursions were limited to ±5° and a wide range reduced forcing frequencies and amplitudes were considered for Re<0.3×106 with various flap deflections and forcing locations. Significant increases in maximum lift and reductions in form drag were attained while simultaneously containing the moment excursions. Oscillatory forcing was found to be far superior to steady blowing and flap-shoulder forcing was found to be superior to leading-edge forcing.",

author = "D. Greenblatt and I. Wygnanski",

note = "Publisher Copyright: {\textcopyright} 1998 by the American Institute of Aeronautics and Astronautics Inc. All rights reserved.; 36th AIAA Aerospace Sciences Meeting and Exhibit, 1998 ; Conference date: 12-01-1998 Through 15-01-1998",

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doi = "10.2514/6.1998-676",

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AU - Greenblatt, D.

AU - Wygnanski, I.

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N2 - A parametric study was undertaken to investigate the effect of oscillatory forcing (with zero net mass-flux) on an airfoil undergoing pitch oscillations at rotorcraft reduced frequencies. The primary objective of the study was to maximize the airfoil performance while simultaneously limiting moment excursions to typical pre-stalled conditions. The incidence angle excursions were limited to ±5° and a wide range reduced forcing frequencies and amplitudes were considered for Re<0.3×106 with various flap deflections and forcing locations. Significant increases in maximum lift and reductions in form drag were attained while simultaneously containing the moment excursions. Oscillatory forcing was found to be far superior to steady blowing and flap-shoulder forcing was found to be superior to leading-edge forcing.

AB - A parametric study was undertaken to investigate the effect of oscillatory forcing (with zero net mass-flux) on an airfoil undergoing pitch oscillations at rotorcraft reduced frequencies. The primary objective of the study was to maximize the airfoil performance while simultaneously limiting moment excursions to typical pre-stalled conditions. The incidence angle excursions were limited to ±5° and a wide range reduced forcing frequencies and amplitudes were considered for Re<0.3×106 with various flap deflections and forcing locations. Significant increases in maximum lift and reductions in form drag were attained while simultaneously containing the moment excursions. Oscillatory forcing was found to be far superior to steady blowing and flap-shoulder forcing was found to be superior to leading-edge forcing.

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M3 - Paper

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T2 - 36th AIAA Aerospace Sciences Meeting and Exhibit, 1998

Y2 - 12 January 1998 through 15 January 1998

ER -

Dynamic stall control by oscillatory forcing

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