Scaling Effects of an Aerodynamic Plasma Actuator

By Mehul P. Patel, T. Ng, Srikanth Vasudevan, Thomas C. Corke, Martiqua L. Post, Thomas McLaughlin, Charles Suchomel. 2007

150 citations recorded by the source corpus.

Subfields: Aerospace Engineering, Computational Mechanics

View Paper: https://www.semanticscholar.org/paper/93026e472d16894b804d6b7c856ab95be57cebed

How researchers see this paper

The researchers whose trusted networks rank it highest, strongest advocate first. Every researcher gets a different order.

In Aerospace Engineering

1. Igor V. Adamovich
2. Mohammad Samimy
3. J. Little
4. M. Nishihara
5. K. Takashima
6. Marios Kotsonis

In Computational Mechanics

1. Igor V. Adamovich
2. Mohammad Samimy
3. K. Takashima
4. M. Nishihara
5. J. Little

Citations in the corpus

• High-lift airfoil trailing edge separation control using a single dielectric barrier discharge plasma actuator (2010, background): “More recently, claims of control authority for freestream velocities as high as 60 m/s with Re = 10(6) have been presented in the literature (Patel et al. 2008).”
• Separation control with nanosecond-pulse-driven dielectric barrier discharge plasma actuators (2012, background): “They have been demonstrated for airfoil leading-edge separation control at freestream velocities up to 60 m=s (Re 10(6)) [4].”
• Single dielectric barrier discharge plasma enhanced aerodynamics: physics, modeling and applications (2009, unknown): “This has been demonstrated on a number of 2-D airfoil shapes including NACA 0009, 0012, 0021, 663 − 018, and a HS3412, as well as highly swept 3-D wing models such as the NASA 1303 planform[83, 82, 81].”