Aerodynamic Stall Control of a Generic Airfoil using Synthetic Jet Actuator
The aerodynamic stall control of a baseline 13-percent
thick NASA GA(W)-2 airfoil using a synthetic jet actuator (SJA) is
presented in this paper. Unsteady Reynolds-averaged Navier-Stokes
equations are solved on a hybrid grid using a commercial software to
simulate the effects of a synthetic jet actuator located at 13% of the
chord from the leading edge at a Reynolds number Re = 2.1x106 and
incidence angles from 16 to 22 degrees. The experimental data for the
pressure distribution at Re = 3x106 and aerodynamic coefficients at
Re = 2.1x106 (angle of attack varied from -16 to 22 degrees) without
SJA is compared with the computational fluid dynamic (CFD)
simulation as a baseline validation. A good agreement of the CFD
simulations is obtained for aerodynamic coefficients and pressure
distribution.
A working SJA has been integrated with the baseline airfoil and
initial focus is on the aerodynamic stall control at angles of attack
from 16 to 22 degrees. The results show a noticeable improvement in
the aerodynamic performance with increase in lift and decrease in
drag at these post stall regimes.
[1] Daniel P. Raymer, Aircraft Design: A Conseptual Approach. 3rd edition.
AIAA Education Series, Reston, VA, 1999, pp. 39.
[2] Robert J. McGhee, William D. Beasley, and Dan M. Somers, "Low
Speed Aerodynamic Characteristics of a 13-Percent-Thick Airfoil
Section designed for General Aviation Applications," NASA TM X-
72697, NASA Langley Research Center, Hampton, Virginia.
[3] Hassan A, Straub F, BD C., "Effects of Surface Blowing/Suction on the
Aerodynamics of Helicopter Rotor Blade-Vortex Interactions-a
Numerical Simulation", Journal of American Helicopter Society
1997,182-194.
[4] Seifert A, Darabi A, Wygnanski I. Delay of airfoil Stall by Periodic
Excitation. AIAA Journal, Vol. 33, No. 4, 1996, pp. 691-707.
[5] Ingard, U., "On the Theory and Design of Acoustic Resonators." The
Journal of the Acoustical Society of America, Vol. 25, No. 6, 1953, pp.
1037-1060.
[6] Barton L. Smith and Ari Glezer, "The Formationand Evolution of
Synthetic jets", Physics of Fluids, vol. 10, No. 9, 1998, pp. 2281-2297.
[7] Smith, B. and Glezer, A., "Jet Vectoring Using Synthetic Jet Actuators,"
Journal of Fluid Mechanics, Vol. 458, 2002, pp. 1-34.
[8] Amitay, M., Smith, D., Kibens, V., Parekh, A. and Glezer, A.,
Aerodynamic flow control over an unconventional airfoil using
synthetic jet actuators" AIAA Journal, Vol. 39, No. 3, pp. 361-370,
March 2001.
[9] Glezer, A. and Amitay, M., "Synthetic Jets," Annual Review of Fluid
Mechanics, Vol. 34, 2002, pp. 503-529.
[10] Gilarranz, J. L., Traub, L. W. & Rediniotis, O. K., "A New Class of
Synthetic Jet Actuators - Part II: Application to Flow Separation
Control," ASME Journal of Fluids Engineering, 127, 2005, pp. 377-
387.
[11] Omar D. Lopez and Robert D. Moser, "Delayed Detached Eddy
Simulation of Flow over an Airfoil", Asociación Argentina de Mecánica
Computacional Vol. XXVII, 2008, pp. 3225-3245.
[12] Kevin E. Wu and Kenneth S. Breuer, "Dynamics of Synthetic Jet
Actuator Arrays for Flow Control", AIAA, 2003.
[13] D. You and P. Moin, "Study of Flow Separation over an Airfoil with
Synthetic Jet Control using Large-Eddy Simulation," Center for
Turbulence Research, Annual Research Briefs 2007.
[14] R. Duvigneau and M. Visonneau, "Optimization of a Synthetic Jet
Actuator for Aerodynamic Stall Control", Computers & Fluids, Vol. 35,
No 6, pp 624-638, July 2006
[15] R. Duvigneau and M. Visonneau, "Simulation and Optimization of Stall
Control for an Airfoil with a Synthetic Jet," Aerospace Science &
technology, Vol. 10, No 4, pp 279-287, May 2006
[16] D. You and P. Moin, "Large-Eddy Simulation of Flow Separation over
an Airfoil with Synthetic Jet Control," Center for Turbulence Research,
Annual Research Briefs 2006.
[17] Guang HONG, "Enabling Micro Synthetic Jet Actuators in Boundary
Layer Separation Control Using Flow Instability," 16th Australasian
Fluid Mechanics Conference, Crown Plaza, Gold Coast, Australia,
2007, pp. 887-891.
[18] Fluent User Manual. (www.fluent.com)
[1] Daniel P. Raymer, Aircraft Design: A Conseptual Approach. 3rd edition.
AIAA Education Series, Reston, VA, 1999, pp. 39.
[2] Robert J. McGhee, William D. Beasley, and Dan M. Somers, "Low
Speed Aerodynamic Characteristics of a 13-Percent-Thick Airfoil
Section designed for General Aviation Applications," NASA TM X-
72697, NASA Langley Research Center, Hampton, Virginia.
[3] Hassan A, Straub F, BD C., "Effects of Surface Blowing/Suction on the
Aerodynamics of Helicopter Rotor Blade-Vortex Interactions-a
Numerical Simulation", Journal of American Helicopter Society
1997,182-194.
[4] Seifert A, Darabi A, Wygnanski I. Delay of airfoil Stall by Periodic
Excitation. AIAA Journal, Vol. 33, No. 4, 1996, pp. 691-707.
[5] Ingard, U., "On the Theory and Design of Acoustic Resonators." The
Journal of the Acoustical Society of America, Vol. 25, No. 6, 1953, pp.
1037-1060.
[6] Barton L. Smith and Ari Glezer, "The Formationand Evolution of
Synthetic jets", Physics of Fluids, vol. 10, No. 9, 1998, pp. 2281-2297.
[7] Smith, B. and Glezer, A., "Jet Vectoring Using Synthetic Jet Actuators,"
Journal of Fluid Mechanics, Vol. 458, 2002, pp. 1-34.
[8] Amitay, M., Smith, D., Kibens, V., Parekh, A. and Glezer, A.,
Aerodynamic flow control over an unconventional airfoil using
synthetic jet actuators" AIAA Journal, Vol. 39, No. 3, pp. 361-370,
March 2001.
[9] Glezer, A. and Amitay, M., "Synthetic Jets," Annual Review of Fluid
Mechanics, Vol. 34, 2002, pp. 503-529.
[10] Gilarranz, J. L., Traub, L. W. & Rediniotis, O. K., "A New Class of
Synthetic Jet Actuators - Part II: Application to Flow Separation
Control," ASME Journal of Fluids Engineering, 127, 2005, pp. 377-
387.
[11] Omar D. Lopez and Robert D. Moser, "Delayed Detached Eddy
Simulation of Flow over an Airfoil", Asociación Argentina de Mecánica
Computacional Vol. XXVII, 2008, pp. 3225-3245.
[12] Kevin E. Wu and Kenneth S. Breuer, "Dynamics of Synthetic Jet
Actuator Arrays for Flow Control", AIAA, 2003.
[13] D. You and P. Moin, "Study of Flow Separation over an Airfoil with
Synthetic Jet Control using Large-Eddy Simulation," Center for
Turbulence Research, Annual Research Briefs 2007.
[14] R. Duvigneau and M. Visonneau, "Optimization of a Synthetic Jet
Actuator for Aerodynamic Stall Control", Computers & Fluids, Vol. 35,
No 6, pp 624-638, July 2006
[15] R. Duvigneau and M. Visonneau, "Simulation and Optimization of Stall
Control for an Airfoil with a Synthetic Jet," Aerospace Science &
technology, Vol. 10, No 4, pp 279-287, May 2006
[16] D. You and P. Moin, "Large-Eddy Simulation of Flow Separation over
an Airfoil with Synthetic Jet Control," Center for Turbulence Research,
Annual Research Briefs 2006.
[17] Guang HONG, "Enabling Micro Synthetic Jet Actuators in Boundary
Layer Separation Control Using Flow Instability," 16th Australasian
Fluid Mechanics Conference, Crown Plaza, Gold Coast, Australia,
2007, pp. 887-891.
[18] Fluent User Manual. (www.fluent.com)
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:63804", author = "Basharat Ali Haider and Naveed Durrani and Nadeem Aizud and Salimuddin Zahir", title = "Aerodynamic Stall Control of a Generic Airfoil using Synthetic Jet Actuator", abstract = "The aerodynamic stall control of a baseline 13-percent
thick NASA GA(W)-2 airfoil using a synthetic jet actuator (SJA) is
presented in this paper. Unsteady Reynolds-averaged Navier-Stokes
equations are solved on a hybrid grid using a commercial software to
simulate the effects of a synthetic jet actuator located at 13% of the
chord from the leading edge at a Reynolds number Re = 2.1x106 and
incidence angles from 16 to 22 degrees. The experimental data for the
pressure distribution at Re = 3x106 and aerodynamic coefficients at
Re = 2.1x106 (angle of attack varied from -16 to 22 degrees) without
SJA is compared with the computational fluid dynamic (CFD)
simulation as a baseline validation. A good agreement of the CFD
simulations is obtained for aerodynamic coefficients and pressure
distribution.
A working SJA has been integrated with the baseline airfoil and
initial focus is on the aerodynamic stall control at angles of attack
from 16 to 22 degrees. The results show a noticeable improvement in
the aerodynamic performance with increase in lift and decrease in
drag at these post stall regimes.", keywords = "Active flow control, Aerodynamic stall, Airfoilperformance, Synthetic jet actuator.", volume = "4", number = "9", pages = "909-6", }
