TY - JOUR
T1 - Maneuvering aspects and 3D effects of active airfoil flow control
AU - Timor, Itay
AU - Ben-Hamou, Eli
AU - Guy, Yair
AU - Seifert, Avi
N1 - Funding Information:
Acknowledgement The experiment was conducted at the Meadow-Knapp low-speed wind tunnel at the Tel-Aviv University, Mary and Steve Meadow Aerodynamics laboratory. Partial funding from the Meadow fund and the Israeli Science foundation special equipment initiation fund are appreciated. Support from TAU technical staff, E. Kronish, A. Blas and S. Paster, M. Vasserman and E. Nevo is greatly appreciated. Thanks are also due to I. Fono and K. Cohen for expertise, support and encouragement.
PY - 2007/6
Y1 - 2007/6
N2 - An active flow control experiment was conducted on a cropped NACA 0018 airfoil to study 3D effects and maneuverability aspects made possible by a segmented actuation system installed in the airfoil. The 14 piezo-fluidic actuators were installed at the corner of the cropped region, inclined at 30° to the local surface, facing downstream. Operating all actuators at unison significantly increased lift and generated a pitch-down moment. Operating all actuators at the same magnitude but varying the phase along the span generated larger lift-increment, with respect to the uniform phase excitation. Significant rolling moment can be generated when only half-span of the wing is actuated. The latter effect, as indicated by the 3D pressure distribution, persists to the leading edge even though the excitation was introduced close to the trailing edge. When a pair, out of the possible fourteen actuators is not operating, very little of the control authority is lost. This is an important finding when issues like fault tolerance and robustness of fluidic-piezo actuators are considered.
AB - An active flow control experiment was conducted on a cropped NACA 0018 airfoil to study 3D effects and maneuverability aspects made possible by a segmented actuation system installed in the airfoil. The 14 piezo-fluidic actuators were installed at the corner of the cropped region, inclined at 30° to the local surface, facing downstream. Operating all actuators at unison significantly increased lift and generated a pitch-down moment. Operating all actuators at the same magnitude but varying the phase along the span generated larger lift-increment, with respect to the uniform phase excitation. Significant rolling moment can be generated when only half-span of the wing is actuated. The latter effect, as indicated by the 3D pressure distribution, persists to the leading edge even though the excitation was introduced close to the trailing edge. When a pair, out of the possible fourteen actuators is not operating, very little of the control authority is lost. This is an important finding when issues like fault tolerance and robustness of fluidic-piezo actuators are considered.
KW - Airfoil
KW - Flow control
KW - Guidance
KW - Mild manuvering
UR - http://www.scopus.com/inward/record.url?scp=34547447210&partnerID=8YFLogxK
U2 - 10.1007/s10494-006-9065-z
DO - 10.1007/s10494-006-9065-z
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AN - SCOPUS:34547447210
VL - 78
SP - 429
EP - 443
JO - Flow, Turbulence and Combustion
JF - Flow, Turbulence and Combustion
SN - 1386-6184
IS - 3-4
ER -