**6. References**

	- [13] Chandrasekhara, M. [2007]. Compressible dynamic stall vorticity flux control using a dynamic camber airfoil, *Sadhana* 32(1-2): 93–102.
	- [14] Chandrasekhara, M. [2010]. Optimum Gurney flap height determination for lost-lift recovery in compressible dynamic stall control, *Aerospace Science and Technology* 14(8): 551–556.
	- [15] Chopra, I. [2002]. Review of State of Art of Smart Structures and Integrated Systems, *AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference, Seattle, WA, AIAA Journal* 40(11).
	- [16] CleanSky [2012]. Clean Sky Joint Technology Initiative, *http://www.cleansky.eu* .
	- [17] Duvigneau, R. & Visonneau, M. [2006]. Simulation and optimization of stall control for an airfoil with a synthetic jet, *Aerospace Science and Technology* 10(4): 279–287.
	- [18] Friedmann, P., de Terlizzi, M. & Myrtle, T. [2001]. New developments in vibration reduction with actively controlled trailing edge flaps, *Mathematical and Computer Modelling* 33(10-11): 1055–1083.
	- [19] Gandhi, F. & Anusonti-Inthra, P. [2008]. Skin design studies for variable camber morphing airfoils, *Smart Materials and Structures* 17(1): 015025.
	- [20] Gandhi, F., Frecker, M. & Nissly, A. [2008]. Design Optimization of a Controllable Camber Rotor Airfoil, *AIAA Journal* 46(1): 142–153.
	- [21] Geissler, W. & Trenker, M. [2002]. Numerical investigation of dynamic stall control by a nose-drooping device, *Technical Report C*.
	- [22] Gordon Leishman, J. [2006]. *Principles of Helicopter Aerodynamics*.
	- [23] Greenblatt, D. & Wygnanski, I. [2000]. The control of flow separation by periodic excitation, *Progress in Aerospace Science* 36.
	- [24] Haber, A. & Jacklin, S. [2002]. Development, manufacturing, and component testing of an individual blade control system for a UH-60 Helicopter Rotor, *American Helicopter* .
	- [25] Head, E. [2012]. Blade Trouble | Vertical Helicopter News.
	- [26] Hong, G. [2006]. Effectiveness of micro synthetic jet actuator enhanced by flow instability in controlling laminar separation caused by adverse pressure gradient, *Sensors And Actuators* 132(2006): 607–615.
	- [27] Kim, J.-S., Wang, K. & Smith, E. [2007]. Development of a resonant trailing-edge flap actuation system for helicopter rotor vibration control, *Smart Materials and Structures* 16(6): 2275–2285.
	- [28] Koratkar, N. & Chopra, I. [n.d.]. Wind Tunnel Testing of a Mach-Scaled Rotor Model with Trailing-Edge Flaps, *Journal of the American Helicopter Society* 47(4): 263–272.
	- [29] Kota, S., Ervin, G. & Osborn, R. [2008]. Design and Fabrication of an Adaptive Leading Edge Rotor Blade, *American Helicopter Society Annual Forum* .
	- [30] Kwon, J.-H., Hwang, K.-J., Kim, S.-S., Kim, P.-J. & Kim, C.-S. [n.d.]. Fatigue life evaluation in composite rotor blade of multipurpose helicopter, *Proceedings 6th Russian-Korean International Symposium on Science and Technology. KORUS-2002 (Cat. No.02EX565)*, IEEE, pp. 15–20.
	- [31] Lee, C., Hong, G., Ha, Q. & Mallinson, S. [2003]. A piezoelectrically actuated micro synthetic jet for active flow control, *Sensors And Actuators* 108(April 2003): 168–174.
	- [32] Lee, S. & McAlister, K. [1993]. Characteristics of deformable leading edge for high performance rotor, *AIAA Journal* 35.
	- [33] Lee, T. & Chopra, I. [2001]. Design of a piezostack driven trailing-edge flap actuator for helicopter rotors, *Smart Mater. Struct.* 10: 15–24.
	- [34] LePage, L. [1936]. Flight on rotating wings, *Journal of the Franklin Institute* 222.

[35] Lim, I.-G. & Lee, I. [2009]. Aeroelastic analysis of rotor systems using trailing edge flaps, *Journal of Sound and Vibration* 321(3-5): 525–536.

20 Will-be-set-by-IN-TECH

[13] Chandrasekhara, M. [2007]. Compressible dynamic stall vorticity flux control using a

[14] Chandrasekhara, M. [2010]. Optimum Gurney flap height determination for lost-lift recovery in compressible dynamic stall control, *Aerospace Science and Technology*

[15] Chopra, I. [2002]. Review of State of Art of Smart Structures and Integrated Systems, *AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference,*

[17] Duvigneau, R. & Visonneau, M. [2006]. Simulation and optimization of stall control for an airfoil with a synthetic jet, *Aerospace Science and Technology* 10(4): 279–287. [18] Friedmann, P., de Terlizzi, M. & Myrtle, T. [2001]. New developments in vibration reduction with actively controlled trailing edge flaps, *Mathematical and Computer*

[19] Gandhi, F. & Anusonti-Inthra, P. [2008]. Skin design studies for variable camber

[20] Gandhi, F., Frecker, M. & Nissly, A. [2008]. Design Optimization of a Controllable

[21] Geissler, W. & Trenker, M. [2002]. Numerical investigation of dynamic stall control by a

[23] Greenblatt, D. & Wygnanski, I. [2000]. The control of flow separation by periodic

[24] Haber, A. & Jacklin, S. [2002]. Development, manufacturing, and component testing of an individual blade control system for a UH-60 Helicopter Rotor, *American Helicopter* .

[26] Hong, G. [2006]. Effectiveness of micro synthetic jet actuator enhanced by flow instability in controlling laminar separation caused by adverse pressure gradient, *Sensors And*

[27] Kim, J.-S., Wang, K. & Smith, E. [2007]. Development of a resonant trailing-edge flap actuation system for helicopter rotor vibration control, *Smart Materials and Structures*

[28] Koratkar, N. & Chopra, I. [n.d.]. Wind Tunnel Testing of a Mach-Scaled Rotor Model with

[29] Kota, S., Ervin, G. & Osborn, R. [2008]. Design and Fabrication of an Adaptive Leading

[30] Kwon, J.-H., Hwang, K.-J., Kim, S.-S., Kim, P.-J. & Kim, C.-S. [n.d.]. Fatigue life evaluation in composite rotor blade of multipurpose helicopter, *Proceedings 6th Russian-Korean International Symposium on Science and Technology. KORUS-2002 (Cat. No.02EX565)*, IEEE,

[31] Lee, C., Hong, G., Ha, Q. & Mallinson, S. [2003]. A piezoelectrically actuated micro synthetic jet for active flow control, *Sensors And Actuators* 108(April 2003): 168–174. [32] Lee, S. & McAlister, K. [1993]. Characteristics of deformable leading edge for high

[33] Lee, T. & Chopra, I. [2001]. Design of a piezostack driven trailing-edge flap actuator for

[34] LePage, L. [1936]. Flight on rotating wings, *Journal of the Franklin Institute* 222.

Trailing-Edge Flaps, *Journal of the American Helicopter Society* 47(4): 263–272.

Edge Rotor Blade, *American Helicopter Society Annual Forum* .

[16] CleanSky [2012]. Clean Sky Joint Technology Initiative, *http://www.cleansky.eu* .

morphing airfoils, *Smart Materials and Structures* 17(1): 015025.

[22] Gordon Leishman, J. [2006]. *Principles of Helicopter Aerodynamics*.

[25] Head, E. [2012]. Blade Trouble | Vertical - Helicopter News.

Camber Rotor Airfoil, *AIAA Journal* 46(1): 142–153.

nose-drooping device, *Technical Report C*.

excitation, *Progress in Aerospace Science* 36.

dynamic camber airfoil, *Sadhana* 32(1-2): 93–102.

14(8): 551–556.

*Seattle, WA, AIAA Journal* 40(11).

*Modelling* 33(10-11): 1055–1083.

*Actuators* 132(2006): 607–615.

performance rotor, *AIAA Journal* 35.

helicopter rotors, *Smart Mater. Struct.* 10: 15–24.

16(6): 2275–2285.

pp. 15–20.

	- [56] Straub, F., Ngo, H. T., Anand, V. & Domzalski, D. [2001]. Development of a Piezoelectric Actuator for Trailing Edge Flap Control of Full Scale Rotor Blades, *Smart Materials and Structures, Vol. 10, No.* 1: 101088/0964–1726/10/1/303.
	- [57] Sturzebecher, D. & Nitsche, W. [2003]. Active cancellation of TollmienâA ¸ ˘ SSchlichting instabilities on a wing using multi-channel sensor actuator systems, *International Journal of Heat and Fluid Flow* 24(4): 572–583.
	- [58] Thakkar, D. & Ganguli, R. [2007]. Induced shear actuation of helicopter rotor blade for active twist control, *Thin-Walled Structures* 45(1): 111–121.
	- [59] Thiel, M. [2006]. *Actuation of an active Gurney flap for rotorcraft applications*, PhD thesis, The Pennsylvania State University.
	- [60] Thiel, M. & Lesieutre, G. [2009]. New Actuation Methods for Miniature Trailing-Edge Effectors for Rotorcraft, *AIAA/ASME/ASCE/AHS/ASC Structures, Structural Dynamics, and Materials Conference*, number May.
	- [61] Vinogradov, A., Schmidt, V., Tuthill, G. & Bohannan, G. [2004]. Damping and electromechanical energy losses in the piezoelectric polymer PVDF, *Mechanics of Materials* 36(10): 1007–1016.
	- [62] Viswamurthy, S. & Ganguli, R. [2004]. An optimization approach to vibration reduction in helicopter rotors with multiple active trailing edge flaps, *Aerospace Science and Technology* 8(3): 185–194.
	- [63] Wang, J., Li, Y. & Choi, K.-S. [2008]. Gurney flap-Lift enhancement, mechanisms and applications, *Progress in Aerospace Sciences* 44(1): 22–47.
	- [64] Watson, B., Friend, J. & Yeo, L. [2009]. Piezoelectric ultrasonic micro/milli-scale actuators, *Sensors And Actuators* 152: 219–233.
	- [65] Wickramasinghe, V. & Hagood, N. [2004]. Material characterization of active fiber composites for integral twist-actuated rotor blade application, *Smart Materials and Structures* 13(5): 1155–1165.
	- [66] Wilbur, M., Mirick, P., Yeager, W., Langston, C., Cesnik, C. & Shin, S. [n.d.]. Vibratory Loads Reduction Testing of the NASA/Army/MIT Active Twist Rotor, *Journal of the American Helicopter Society* 47(2): 11.
	- [67] Yang, A., Ro, J., Yang, M. & Chang, W. [2009]. Investigation of piezoelectrically generated synthetic jet flow, *Journal of Visualization* 12(1): 9–16.
	- [68] Yee, K., Joo, W. & Lee, D.-H. [2007]. Aerodynamic Performance Analysis of a Gurney Flap for Rotorcraft Application, *Journal of Aircraft* 44(3): 1003–1014.
	- [69] Yu, Y., Gmelin, B. & Splettstoesser, W. [1997]. Reduction of helicopter blade-vortex interaction noise by active rotor control technology, *Progress in Aerospace* 33(97): 647–687.
