Trailing edge flow separation control using Feedback driven Plasma Actuator triggered by fluctuating velocity in the wake of an NACA0012 Airfoil.

2017 ◽  
Vol 2017.23 (0) ◽  
pp. 203
Author(s):  
Tomohiro SHIOTSUKI ◽  
Yosuke HIROBE ◽  
Asei TEZUKA
Keyword(s):  
Flow Separation ◽  
Plasma Actuator ◽  
Separation Control ◽  
Trailing Edge ◽  
Flow Separation Control ◽  
Naca0012 Airfoil ◽  
Edge Flow

Plasma-Actuator Burst-Mode Frequency Effects on Leading-Edge Flow-Separation Control at Reynolds Number 2.6×105

AIAA Journal ◽  
2017 ◽  
Vol 55 (11) ◽  
pp. 3789-3806 ◽  
Author(s):  
Hikaru Aono ◽  
Soshi Kawai ◽  
Taku Nonomura ◽  
Makoto Sato ◽  
Kozo Fujii ◽  
...  
Keyword(s):  
Reynolds Number ◽  
Flow Separation ◽  
Leading Edge ◽  
Plasma Actuator ◽  
Mode Frequency ◽  
Separation Control ◽  
Flow Separation Control ◽  
Frequency Effects ◽  
Burst Mode ◽  
Edge Flow

Development of a MEMS-Based Active Control System for Flow Separation in the Transonic Regime

2000 ◽  
Author(s):  
Steve Tung ◽  
Brant Maines ◽  
Fukang Jiang ◽  
Tom Tsao
Keyword(s):  
Shear Stress ◽  
Control System ◽  
Wind Tunnel ◽  
Flow Separation ◽  
Control Flow ◽  
Separation Control ◽  
Sensors And Actuators ◽  
Trailing Edge ◽  
Flow Separation Control ◽  
Mach Numbers

Abstract A MEMS-based active system is currently under development for flow separation control in the transonic regime. The system consists of micro shear stress sensors for flow sensing and micro balloon actuators for separation control. We have successfully completed the first phase of the program in which the micro sensors and actuators were fabricated and tested in a wind tunnel facility. In the test, the sensors and actuators were flush mounted on a 3D model, which is representative of the upper surface of a wing with a deflected trailing edge flap. The model was installed in the wind tunnel and tested at a series of Mach numbers between 0.2 and 0.6. For all Mach numbers, the sensor output indicates that flow separates over the trailing edge when the micro balloons are in the ‘down’ position. When the micro balloons are inflated, the shear stress level on the trailing edge increases substantially, indicating an improvement of the separation characteristics. This result demonstrates the feasibility of using MEMS sensors and actuators to control flow separation. It is the first step toward the development of a revolutionary closed loop flow control system applicable to existing and future aircraft to enhance aerodynamic performance.

Wing Flow Separation Control Using Asymmetrical and Symmetrical Plasma Actuator

2017 ◽  
Vol 54 (1) ◽  
pp. 301-309 ◽  
Author(s):  
Xin Zhang ◽  
Hua-Xing Li ◽  
Yong Huang ◽  
Wan-Bo Wang
Keyword(s):  
Flow Separation ◽  
Plasma Actuator ◽  
Separation Control ◽  
Flow Separation Control

Flow Separation Control by Plasma Actuator with Nanosecond Pulsed-Periodic Discharge

AIAA Journal ◽  
2009 ◽  
Vol 47 (1) ◽  
pp. 168-185 ◽  
Author(s):  
D. V. Roupassov ◽  
A. A. Nikipelov ◽  
M. M. Nudnova ◽  
A. Yu. Starikovskii
Keyword(s):  
Flow Separation ◽  
Plasma Actuator ◽  
Separation Control ◽  
Flow Separation Control ◽  
Periodic Discharge

Numerical study of passive and active flow separation control over a NACA0012 airfoil

2008 ◽  
Vol 37 (8) ◽  
pp. 975-992 ◽  
Author(s):  
Hua Shan ◽  
Li Jiang ◽  
Chaoqun Liu ◽  
Michael Love ◽  
Brant Maines
Keyword(s):  
Flow Separation ◽  
Numerical Study ◽  
Separation Control ◽  
Flow Separation Control ◽  
Naca0012 Airfoil ◽  
Active Flow

Mechanism of flow separation control with DBD plasma actuator obtained by Ape X Deep Q Network Control

2021 ◽  
Author(s):  
Satoshi Shimomura ◽  
Satoshi Sekimoto ◽  
Akira Oyama ◽  
Kozo Fujii ◽  
Hiroyuki Nishida
Keyword(s):  
Flow Separation ◽  
Plasma Actuator ◽  
Network Control ◽  
Separation Control ◽  
Dbd Plasma ◽  
Flow Separation Control
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