Aerodynamic Drag Reduction Investigation for a Simplified Road Vehicle Using Plasma Flow Control

Author(s):  
Bahram Khalighi ◽  
Joanna Ho ◽  
John Cooney ◽  
Brian Neiswander ◽  
Thomas C. Corke ◽  
...  

The effect of plasma flow control on reducing aerodynamic drag for ground vehicles is investigated. The experiments were carried out for a simplified ground vehicle using single dielectric barrier discharge (SDBD) plasma actuators. The plasma actuators were designed to alter the flow structure in the wake region behind the vehicle. The Ahmed body was modified to allow eight different vehicle geometries (with backlight or slant angles of 0° and 35°). Each of these were further modified by rounding the edges with different radii. Flow visualizations such as particle streams and surface oil were used to quantify features of the local flow field. The drag on the models was measured using a force balance as well as by integrating the mean velocity profiles in the model wakes. The results indicated that flow modifications needed to be applied symmetrically (upper to lower and/or side to side). This was demonstrated with the 0° backlight angle (square-back) that had all four side-corners rounded. Plasma actuators were applied to all four of the rounded edges to enhance the ability to direct the flow into the wake. Wake measurements showed that steady actuation at a fixed actuator voltage reduced the drag by an average of 20% at the lower velocities (below 15 m/s) and by 3% at the highest velocity tested (20 m/s). Model constraints prevented increasing the plasma actuator voltage that was needed to maintain the higher drag reduction observed at the lower speeds.

2010 ◽  
Vol 24 (13) ◽  
pp. 1405-1408 ◽  
Author(s):  
ZIJIE ZHAO ◽  
CHAO GAO ◽  
FENG LIU ◽  
SHIJUN LUO

Forward blowing from a pair of plasma actuators on the leeward surface and near the apex is used to switch the asymmetric vortex pair over a cone of semi-apex angle 10° at high angles of attack. Wind tunnel pressure measurements show that by appropriate design of the actuators and appropriate choice of the AC voltage and frequency, side forces and yawing moments of opposite signs can be obtained at a given angle of attack by activating one of the plasma actuators. Further work is suggested.


Author(s):  
Richard Rivir ◽  
A. White ◽  
C. Carter ◽  
B. Ganguly

2013 ◽  
Vol 62 ◽  
pp. 52-78 ◽  
Author(s):  
Jin-Jun Wang ◽  
Kwing-So Choi ◽  
Li-Hao Feng ◽  
Timothy N. Jukes ◽  
Richard D. Whalley

Author(s):  
R Bardera-Mora ◽  
A Conesa ◽  
I Lozano

This experimental investigation presents a new active flow control technique based on plasma actuators applied to a backward facing step whose structure is similar to that formed by the hangar and flight deck of small naval vessels. These experiments were carried out by testing a simple frigate shape model settled at 0° wind over deck in a low-speed wind tunnel. Two different configurations of dielectric barrier discharge plasma actuator have been used to modify the flow downstream of the step. Results obtained investigating the flow by particle image velocimetry prove the capacity of plasma actuators by reducing instabilities and turbulence over the simple frigate shape model.


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