Active Control of Flow Separation Over a NACA0024 Airfoil by DBD Plasma Actuator and FBG Sensor

2011 ◽  
Author(s):  
Seth Walker ◽  
Takehiko Segawa ◽  
Timothy Jukes ◽  
Hirohide Furutani ◽  
Norihiko Iki ◽  
...  
Keyword(s):  
Active Control ◽  
Flow Separation ◽  
Leading Edge ◽  
Open Circuit ◽  
Flow Conditions ◽  
Dbd Plasma ◽  
Flow Separation Control ◽  
Barrier Discharge Plasma ◽  
Tunnel Analysis ◽  
Control Of Flow

Dielectric barrier discharge plasma actuators (DBD-PA) and fiber Bragg grating flow sensors (FBG-FS) have been investigated for active control of flow separation around a NACA0024 airfoil. Tangential jets were produced in the vicinity of the DBD-PA slightly aft of the leading edge of the airfoil. The flow separation control ability was evaluated at a low Reynolds number, Re = 5.0×104, in an open-circuit wind tunnel. Analysis of instantaneous and time-averaged velocity distributions around the airfoil was achieved using a particle image velocimetry (PIV) system. The flow conditions induced by the DBD-PA to suppress the flow separation were found for angles of attack of α = 8°, 12°, and 16°. When unaided by the DBD-PA system, flow separations from NACA0024 airfoil are suppressed significantly for certain Reynolds numbers and angles of attack. FBG-FS attached a chord-wise cantilever near the trailing edge of the airfoil was used to measure strain fluctuations for its feasibility to detect flow separation in real time and construct feedback control system with DBD-PA. In this study, it was found that standard deviations of strain fluctuations increase obviously in cases of flow conditions at which the flow around NACA0024 airfoil separates.

scholarly journals Flow Separation Control of Backward-Facing Step Airfoil NACA0015 by Blowing Technique

2019 ◽  
Vol 12 (1) ◽  
pp. 99-119
Author(s):  
Khuder N. Abed
Keyword(s):  
Flow Separation ◽  
Numerical Study ◽  
Leading Edge ◽  
Distribution Coefficients ◽  
Open Circuit ◽  
Experimental Investigations ◽  
Backward Facing Step ◽  
Ansys Fluent ◽  
Flow Separation Control ◽  
Naca 0015

The aim of this paper is to control the flow separation above backward-facing step (BFS) airfoil type NACA 0015 by blowing method. The flow field over airfoil has been studied both experimentally and computationally. The study was divided into two parts: a practical study through which NACA 0015 type with a backward -facing step (located at 44.4% c from leading edge) on the upper surface containing blowing holes parallel to the airfoil chord was used. The tests were done over two-dimensional airfoil in an open circuit suction subsonic wind tunnel with flow velocity 25m/s to obtain the pressure distribution coefficients. A numerical study was done by using ANSYS Fluent software version 16.0 on three models of NACA 0015, the first one has backward-facing step without blowing, the second with single blowing holes and the third have multi blowing holes technique. Both studies (experimental and numerical) were done at low Reynolds number (Re=4.4x105) and all models have chord length 0.27m.The experimental investigations and CFD simulations have been performed on the same geometry dimensions, it has been observed that the flow separation on the airfoil can be delayed by using  velocity blowing (30m/s) on the upper surface. The multi blowing holes with velocity improved the aerodynamics properties.The multi blowing holes and single blowing hole thesame effect onpressure distribution coefficients

Active Control of Flow Separation from Supercritical Airfoil Leading-Edge Flap Shoulder

2005 ◽  
Vol 42 (5) ◽  
pp. 1142-1149 ◽  
Author(s):  
LaTunia Pack Melton ◽  
Norman W. Schaeffler ◽  
Chung-Sheng Yao ◽  
Avi Seifert
Keyword(s):  
Active Control ◽  
Flow Separation ◽  
Leading Edge ◽  
Supercritical Airfoil ◽  
Control Of Flow

scholarly journals Feedback Control of Flow Separation Using Plasma Actuator and FBG Sensor

2016 ◽  
Vol 2016 ◽  
pp. 1-16 ◽  
Author(s):  
Takehiko Segawa ◽  
Daiki Suzuki ◽  
Takayasu Fujino ◽  
Timothy Jukes ◽  
Takayuki Matsunuma
Keyword(s):  
Feedback Control ◽  
Flow Separation ◽  
Side Wall ◽  
Leading Edge ◽  
Plasma Actuator ◽  
Dbd Plasma ◽  
Pressure Surface ◽  
String Type ◽  
Fbg Sensor ◽  
Control Of Flow

A feedback control system for mitigating flow separation was developed by using a string-type dielectric-barrier-discharge (DBD) plasma actuator and a fiber Bragg grating (FBG) sensor. Tangential jets were induced from the string-type DBD plasma actuator, which was located at 5% chord from the leading edge of an NACA0024 airfoil. The FBG sensor was attached to the interior surface near the root of the cantilever beam modeled on the pressure surface of the airfoil. The strain at the cantilever root was reflected in the form of Bragg wavelengths (λB) detected by the FBG sensor when the cantilever tip was vibrated by the flow near the trailing edge of the airfoil. It was found that calculating running standard deviations in the Bragg wavelength (λB′) detected by the sensor was valuable for judging flow separation in real time. The feedback control of flow separation on the NACA0024 airfoil was successfully demonstrated by setting λB′=0.0028 with periodic flow separations generated in a wind tunnel by oscillating a side wall of the test section with frequency fw=0.42 Hz. It was confirmed that the appearance probability of flow separation tends to decrease with a decrease in the duration for calculating λB′ and with an increase in the duration of jet injection.

Active Control of Flow Separation on a Hemisphere with Plasma Forcing

2011 ◽  
Author(s):  
Haris Catrakis ◽  
Tsolag Apelian ◽  
Oleg Goushcha ◽  
Alejandro Puga ◽  
David Hartwig
Keyword(s):  
Active Control ◽  
Flow Separation ◽  
Control Of Flow
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