scholarly journals Airfoil flow separation control with plasma synthetic jets at moderate Reynolds number

2018 ◽  
Vol 59 (11) ◽  
Author(s):  
Haohua Zong ◽  
Timo van Pelt ◽  
Marios Kotsonis
Keyword(s):  
Reynolds Number ◽  
Flow Separation ◽  
Synthetic Jets ◽  
Separation Control ◽  
Flow Separation Control ◽  
Moderate Reynolds Number ◽  
Airfoil Flow

Coupled Blowing and Suction for Flow Separation Control

2019 ◽  
Author(s):  
M. Tadjfar ◽  
D. J. Kamari
Keyword(s):  
Boundary Layer ◽  
Reynolds Number ◽  
Flow Field ◽  
Turbulence Model ◽  
Flow Separation ◽  
Active Flow Control ◽  
Suction Side ◽  
Separation Control ◽  
Flow Separation Control ◽  
Active Flow

Abstract The effects of applying a coupled unsteady blowing and suction combination over SD7003 airfoil at Reynolds number of 60,000 at an angle of attack of 13°, where a large separation on the suction side of the airfoil existed, was considered to investigate active flow control (AFC) mechanism. URANS equations were employed to solve the flow field and k–ω SST was used as the turbulence model. The unsteady blowing and suction were implemented at an angle to the surface crossing the boundary layer (CBL). The influence of location and frequency of the blowing/suction jets were examined.

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

scholarly journals Fluidic-Oscillator-Based Pulsed Jet Actuators for Flow Separation Control

Fluids ◽  
2021 ◽  
Vol 6 (4) ◽  
pp. 166
Author(s):  
Stephan Löffler ◽  
Carola Ebert ◽  
Julien Weiss
Keyword(s):  
Flow Separation ◽  
Oscillation Frequency ◽  
Current Knowledge ◽  
Industrial Applications ◽  
Synthetic Jets ◽  
Separation Control ◽  
Test Surface ◽  
Flow Separation Control ◽  
Pulsed Jet ◽  
Jet Actuators

The control of flow separation on aerodynamic surfaces remains a fundamental goal for future air transportation. On airplane wings and control surfaces, the effects of flow separation include decreased lift, increased drag, and enhanced flow unsteadiness and noise, all of which are detrimental to flight performance, fuel consumption, and environmental emissions. Many types of actuators have been designed in the past to counter the negative effects of flow separation, from passive vortex generators to active methods like synthetic jets, plasma actuators, or sweeping jets. At the Chair of Aerodynamics at TU Berlin, significant success has been achieved through the use of pulsed jet actuators (PJA) which operate by ejecting a given amount of fluid at a specified frequency through a slit-shape slot on the test surface, thereby increasing entrainment and momentum in a separating boundary layer and thus delaying flow separation. Earlier PJAs were implemented using fast-switching solenoid valves to regulate the jet amplitude and frequency. In recent years, the mechanical valves have been replaced by fluidic oscillators (FO) in an attempt to generate the desired control authority without any moving parts, thus paving the way for future industrial applications. In the present article, we present in-depth flow and design analysis which affect the operation of such FO-based PJAs. We start by reviewing current knowledge on the mechanism of flow separation control with PJAs before embarking on a detailed analysis of single-stage FO-based PJAs. In particular, we show that there is a fundamental regime where the oscillation frequency is mainly driven by the feedback loop length. Additionally, there are higher-order regimes where the oscillation frequency is significantly increased. The parameters that influence the oscillation in the different regimes are discussed and a strategy to incorporate this new knowledge into the design of future actuators is proposed.

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