Abstract
A turbulent compressible Mach 0.6 jet was used as a test bed for applying closed loop flow control schemes, with the control objective of reduction of the far-field noise signature. The Reynolds number, based on a nozzle exit diameter of 0.0508m, is 690,000. An azimuthal array of eight zero-net mass flux piezo-electric jets, placed at the jet exit, was used for control authority. The actuators were driven at 1900Hz, corresponding to an exit velocity ≈ 50m/s from each actuator. Three control cases were tested, an open loop mode-0 excitation, a closed loop mode-0 (column mode) excitation, and a closed loop mode-1 (helical mode) excitation. A spatial Fourier azimuthal decomposition of the near-field hydrodynamic pressure at 8D in the stream wise is used for state estimation and feedback. The far-field sound was measured with six microphones oriented along a boom at increasing polar angles from φ= 15°-90° at 75D downstream to evaluate the effectiveness of each controlled case. For φ = 15° (shallow angle), an overall increase in the sound at lower Strouhal numbers (0.04 - 0.2) of the jet was noticed for all controlled cases. The greatest reduction was noticed for the closed loop mode-0 case. Conversely, an overall decrease in the sound was noticed at higher jet Strouhal numbers (0.2 - 3.7). At φ = 60° and 90°, there was an overall increase in farfield sound for all controlled cases.
| Original language | English (US) |
|---|---|
| Title of host publication | 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition |
| State | Published - 2009 |
| Event | 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition - Orlando, FL, United States Duration: Jan 5 2009 → Jan 8 2009 |
Other
| Other | 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition |
|---|---|
| Country | United States |
| City | Orlando, FL |
| Period | 1/5/09 → 1/8/09 |
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ASJC Scopus subject areas
- Space and Planetary Science
- Aerospace Engineering
Cite this
Closed-loop control of a turbulent compressible Mach 0.6 Jet. / Low, Kerwin R.; Andino, Marlyn Y.; Wallace, Ryan M.; Hall, Andre M.; Glauser, Mark N.
47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition. 2009. 2009-0854.Research output: Chapter in Book/Report/Conference proceeding › Conference contribution
}
TY - GEN
T1 - Closed-loop control of a turbulent compressible Mach 0.6 Jet
AU - Low, Kerwin R.
AU - Andino, Marlyn Y.
AU - Wallace, Ryan M.
AU - Hall, Andre M.
AU - Glauser, Mark N
PY - 2009
Y1 - 2009
N2 - A turbulent compressible Mach 0.6 jet was used as a test bed for applying closed loop flow control schemes, with the control objective of reduction of the far-field noise signature. The Reynolds number, based on a nozzle exit diameter of 0.0508m, is 690,000. An azimuthal array of eight zero-net mass flux piezo-electric jets, placed at the jet exit, was used for control authority. The actuators were driven at 1900Hz, corresponding to an exit velocity ≈ 50m/s from each actuator. Three control cases were tested, an open loop mode-0 excitation, a closed loop mode-0 (column mode) excitation, and a closed loop mode-1 (helical mode) excitation. A spatial Fourier azimuthal decomposition of the near-field hydrodynamic pressure at 8D in the stream wise is used for state estimation and feedback. The far-field sound was measured with six microphones oriented along a boom at increasing polar angles from φ= 15°-90° at 75D downstream to evaluate the effectiveness of each controlled case. For φ = 15° (shallow angle), an overall increase in the sound at lower Strouhal numbers (0.04 - 0.2) of the jet was noticed for all controlled cases. The greatest reduction was noticed for the closed loop mode-0 case. Conversely, an overall decrease in the sound was noticed at higher jet Strouhal numbers (0.2 - 3.7). At φ = 60° and 90°, there was an overall increase in farfield sound for all controlled cases.
AB - A turbulent compressible Mach 0.6 jet was used as a test bed for applying closed loop flow control schemes, with the control objective of reduction of the far-field noise signature. The Reynolds number, based on a nozzle exit diameter of 0.0508m, is 690,000. An azimuthal array of eight zero-net mass flux piezo-electric jets, placed at the jet exit, was used for control authority. The actuators were driven at 1900Hz, corresponding to an exit velocity ≈ 50m/s from each actuator. Three control cases were tested, an open loop mode-0 excitation, a closed loop mode-0 (column mode) excitation, and a closed loop mode-1 (helical mode) excitation. A spatial Fourier azimuthal decomposition of the near-field hydrodynamic pressure at 8D in the stream wise is used for state estimation and feedback. The far-field sound was measured with six microphones oriented along a boom at increasing polar angles from φ= 15°-90° at 75D downstream to evaluate the effectiveness of each controlled case. For φ = 15° (shallow angle), an overall increase in the sound at lower Strouhal numbers (0.04 - 0.2) of the jet was noticed for all controlled cases. The greatest reduction was noticed for the closed loop mode-0 case. Conversely, an overall decrease in the sound was noticed at higher jet Strouhal numbers (0.2 - 3.7). At φ = 60° and 90°, there was an overall increase in farfield sound for all controlled cases.
UR - http://www.scopus.com/inward/record.url?scp=78549267893&partnerID=8YFLogxK
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M3 - Conference contribution
AN - SCOPUS:78549267893
SN - 9781563479694
BT - 47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition
ER -