Active flow control of a delta wing at high incidence using segmented piezoelectric actuators

S. Margalit, D. Greenblatt, A. Seifert, Israel J Wygnanski

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

17 Citations (Scopus)

Abstract

The separated flow around a 60° degrees sweep, semi-span delta wing at high angle-of-attack was controlled using zero-mass-flux periodic excitation, generated by cavity-installed Piezo-electric actuators. The excitation emanated from a segmented slot at the sharp leading edge. Normal and tangential forces, together with pitching and rolling moments, were measured by means of a four-component balance. The boundary layer on the wind tunnel wall, upstream of the delta wing, was removed using suction, with little effect on the forces and moments measured on the semi span model. Amplitude modulation (AM) and burst mode (BM) signals were used to generate reduced frequencies (scaled with the free stream velocity and the root chord) in the range O(1) to O(10) relative to the high resonance frequency of the actuators that is of O(100) based on the same scaling. A parametric investigation, studying the effects of AM frequency, BM duty cycle and frequency, excitation momentum, its location along the leading edge and the optimal phase between the actuators as well as the Reynolds number, is reported and discussed. Upper surface pressures and PIV data supplements the force and moment data. The comprehensive data-set indicates that frequencies of O(1) are most effective for increasing the normal force generated by the delta wing. Burst mode with a duty cycle as low as 5% was more effective than amplitude modulated signal with the same peak velocity but an order of magnitude larger momentum input. Based on the current findings it is not shown that the enhanced performance is related either to delay of vortex breakdown or to vortex enhancement prior to breakdown, but perhaps to a quasi-2D mechanism, enhancing the momentum transfer across the shear layer and generating a streamwise vortex of size commensurable to the local wing span.

Original languageEnglish (US)
Title of host publication1st Flow Control Conference
StatePublished - 2002
Externally publishedYes
Event1st Flow Control Conference 2002 - St. Louis, MO, United States
Duration: Jun 24 2002Jun 26 2002

Other

Other1st Flow Control Conference 2002
CountryUnited States
CitySt. Louis, MO
Period6/24/026/26/02

Fingerprint

Piezoelectric actuators
Flow control
Vortex flow
Amplitude modulation
Momentum
Actuators
Momentum transfer
Angle of attack
Wind tunnels
Boundary layers
Reynolds number
Mass transfer

ASJC Scopus subject areas

  • Fluid Flow and Transfer Processes
  • Aerospace Engineering
  • Control and Systems Engineering

Cite this

Margalit, S., Greenblatt, D., Seifert, A., & Wygnanski, I. J. (2002). Active flow control of a delta wing at high incidence using segmented piezoelectric actuators. In 1st Flow Control Conference

Active flow control of a delta wing at high incidence using segmented piezoelectric actuators. / Margalit, S.; Greenblatt, D.; Seifert, A.; Wygnanski, Israel J.

1st Flow Control Conference. 2002.

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

Margalit, S, Greenblatt, D, Seifert, A & Wygnanski, IJ 2002, Active flow control of a delta wing at high incidence using segmented piezoelectric actuators. in 1st Flow Control Conference. 1st Flow Control Conference 2002, St. Louis, MO, United States, 6/24/02.
Margalit S, Greenblatt D, Seifert A, Wygnanski IJ. Active flow control of a delta wing at high incidence using segmented piezoelectric actuators. In 1st Flow Control Conference. 2002
Margalit, S. ; Greenblatt, D. ; Seifert, A. ; Wygnanski, Israel J. / Active flow control of a delta wing at high incidence using segmented piezoelectric actuators. 1st Flow Control Conference. 2002.
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