LOGIN TO YOUR ACCOUNT

Username
Password
Remember Me
Or use your Academic/Social account:

CREATE AN ACCOUNT

Or use your Academic/Social account:

Congratulations!

You have just completed your registration at OpenAire.

Before you can login to the site, you will need to activate your account. An e-mail will be sent to you with the proper instructions.

Important!

Please note that this site is currently undergoing Beta testing.
Any new content you create is not guaranteed to be present to the final version of the site upon release.

Thank you for your patience,
OpenAire Dev Team.

Close This Message

CREATE AN ACCOUNT

Name:
Username:
Password:
Verify Password:
E-mail:
Verify E-mail:
*All Fields Are Required.
Please Verify You Are Human:
fbtwitterlinkedinvimeoflicker grey 14rssslideshare1
Erfani, R.; Zare-Behtash, H.; Kontis, K. (2012)
Publisher: Elsevier
Languages: English
Types: Article
Subjects:
Plasma actuators have become the topic of interest of many researchers for the purpose of flow control. They have the advantage of manipulating the flow without the need for any moving parts, a small surface profile which does not disturb the free stream flow, and the ability to switch them on or off depending on the particular situation (active flow control). Due to these characteristics they are becoming very popular for flow control over aircraft wings. The objective of the current study is to examine the effect of the actuator surface temperature on its performance. This is an important topic to understand when dealing with real life aircraft equipped with plasma actuators. The temperature variations encountered during a flight envelope may have adverse effects in actuator performance. A peltier heater along with dry ice are used to alter the actuator temperature, while particle image velocimetry (PIV) is utilised to analyse the flow field. The results show a significant change in the induced flow field by the actuator as the surface temperature is varied. It is found that for a constant peak-to-peak voltage the maximum velocity produced by the actuator depends directly on the dielectric surface temperature. The findings suggest that by changing the actuator temperature the performance can be maintained or even altered at different environmental conditions.
  • The results below are discovered through our pilot algorithms. Let us know how we are doing!

    • CV1 CV2
    • 44(7):1572-1578, 2006. [12] C.C. Wang and S. Roy. Electrodynamic enhancement of film cooling of turbine blades. Journal
    • of Applied Physics, 104(7):073305, 2008. [13] J. Huang, T.C. Corke, and F.O. Thomas. Plasma actuators for separation control of low-
    • pressure turbine blades. AIAA Journal, 44(1):51-57, 2006. [14] M.L. Post and T.C. Corke. Separation control on high angle of attack airfoil using plasma
    • actuators. AIAA Journal, 42(11):2177-2184, 2004. [15] S. Grundmann and C. Tropea. Delay of Boundary-Layer Transition Using Plasma Actuators.
    • In 46th AIAA Aerospace Sciences Meeting and Exhibit, Paper Number AIAA-2008-1369, 2008. [16] C. He, T.C. Corke, and M.P. Patel. Plasma flaps and slats: an application of weakly ionized
    • plasma actuators. Journal of Aircraft, 46(3):864-873, 2009. [17] M.L. Post and T.C. Corke. Separation control using plasma actuators: dynamic stall vortex
    • control on oscillating airfoil. AIAA Journal, 44(12):3125-3135, 2006. [18] F.O. Thomas, A. Kozlov, and T.C. Corke. Plasma actuators for cylinder flow control and
    • noise reduction. AIAA Journal, 46(8):1921-1931, 2008. [19] M.P. Patel, T.T. Ng, S. Vasudevan, T.C. Corke, and C. He. Plasma actuators for hingeless
    • aerodynamic control of an unmanned air vehicle. Journal of Aircraft, 44(4):1264-1274, 2007. [20] B. Goksel, D. Greenblatt, I. Rechenberg, R. Bannasch, and C.O. Paschereit. Plasma Flow
    • Control at MAV Reynolds Numbers. In 3rd US-European Competition and Workshop on Micro
    • Air Vehicle Systems and European Micro Air Vehicle Conference and Flight Competition, 2007. [21] D.F. Opaits, A.V. Likhanskii, G. Neretti, S. Zaidi, M.N. Shneider, R.B. Miles, and S.O.
    • of Applied Physics, 104(4):043304, 2008. [22] R. Erfani, T. Erfani, S.V. Utyuzhnikov, and K. Kontis. Optimisation of multiple encapsulated
    • electrode plasma actuator. Aerospace Science and Technology, In Press, 2012. [23] N. Benard, N. Balcon, and E. Moreau. Electric wind produced by a surface dielectric barrier
    • Physics D: Applied Physics, 41:042002, 2008. [24] H.D. Vo. Rotating stall suppression in axial compressors with casing plasma actuation. Journal
    • of Propulsion and Power, 26(4):808-818, 2010.
  • No related research data.
  • No similar publications.

Share - Bookmark

Download from

Cite this article