Active flow control of transonic buffet at low Reynolds numbers by electric discharge

2020 ◽  
Author(s):  
P. A. Polivanov ◽  
A. A. Sidorenko
Keyword(s):  
Flow Control ◽  
Electric Discharge ◽  
Active Flow Control ◽  
Reynolds Numbers ◽  
Low Reynolds Numbers ◽  
Low Reynolds ◽  
Active Flow ◽  
Transonic Buffet

scholarly journals Active Flow Control at Low Reynolds Numbers by Periodic Airfoil Morphing

2016 ◽  
Author(s):  
Gareth R. Jones ◽  
Matthew J. Santer ◽  
George Papadakis ◽  
Marco T. Debiasi
Keyword(s):  
Flow Control ◽  
Active Flow Control ◽  
Reynolds Numbers ◽  
Low Reynolds Numbers ◽  
Low Reynolds ◽  
Active Flow

Active Flow Control Upon Cavities At Low Reynolds Numbers

2012 ◽  
Author(s):  
Juan Delnero ◽  
Julio Marañon ◽  
Mariano Martinez ◽  
Jorge Colman ◽  
Mariano Garcia Sainz ◽  
...  
Keyword(s):  
Flow Control ◽  
Active Flow Control ◽  
Reynolds Numbers ◽  
Low Reynolds Numbers ◽  
Low Reynolds ◽  
Active Flow

Features of the Operation of Powered Resonance Tube Actuators: Experiments and Simulations

2003 ◽  
Author(s):  
Ganesh Raman ◽  
Shekhar Sarpotdar ◽  
Alan B. Cain
Keyword(s):  
Flow Control ◽  
Active Flow Control ◽  
Reynolds Numbers ◽  
Detailed Characterization ◽  
Low Reynolds Numbers ◽  
Resonance Tube ◽  
Upstream Direction ◽  
Regular Oscillation ◽  
Active Flow

There has been a recent surge of interest in powered resonance tube actuators for flow control applications. Additional features of powered resonance tube actuators (both experiments and simulations) are presented in this paper. A Powered Resonance Tube (PRT) is a device based on aeroacoustics principles, capable of producing intense perturbation levels for use in active flow control. The PRT described here is capable of producing frequencies ranging from 1600 to 15,000 Hz at amplitudes as high as 160 dB near the source. Our detailed experiments aimed at understanding the PRT phenomenon are complemented by improved direct numerical simulations. We provide a detailed characterization of the unsteady pressures in the nearfield of the actuator using phase averaged pressure measurements. The measurements revealed that propagating fluctuations were biased towards the upstream direction (relative to the supply jet) for some frequencies. However, this feature depended on the frequency at which the device was operated. The simulations that were performed earlier at a Reynolds number 490 times lower than that in the experiment have been refined. The current simulations are performed at 49 times lower than that in the experiments and show that a finer scale structure develops at higher Reynolds numbers and a more regular oscillation is present at low Reynolds numbers.

Low Reynolds Number Laminar Airfoil with Active Flow Control

2010 ◽  
Author(s):  
Michael Thake ◽  
Nathan Packard ◽  
Carlos Bonilla ◽  
Jeffrey Bons
Keyword(s):  
Reynolds Number ◽  
Flow Control ◽  
Low Reynolds Number ◽  
Active Flow Control ◽  
Low Reynolds ◽  
Active Flow

Research of the suction flow control on wings at low Reynolds numbers

2017 ◽  
Vol 232 (8) ◽  
pp. 1515-1528 ◽  
Author(s):  
Dongli Ma ◽  
Guanxiong Li ◽  
Muqing Yang ◽  
Shaoqi Wang
Keyword(s):  
Flow Control ◽  
Aerodynamic Force ◽  
Separation Bubble ◽  
Reynolds Numbers ◽  
Aerodynamic Characteristics ◽  
Flow State ◽  
Laminar Separation ◽  
Low Reynolds Numbers ◽  
Low Reynolds ◽  
Suction Flow

Laminar separation and transition have significant effects on aerodynamic characteristics of the wing under the condition of low Reynolds numbers. Using the flow control methods to delay and eliminate laminar separation has great significance. This study uses the method combined with water tunnel test and numerical calculation to research the effects of suction flow control on the flow state and aerodynamic force of the wing at low Reynolds numbers. The effects of suction flow rate and suction location on laminar separation, transition and aerodynamic performance of the wing are further researched. The results of the research show that, the suction can control laminar separation and transition effectively, when the suction holes are in the interior of the separation bubble, and close to the separation point, the suction has the best control effect. When the Reynolds number is Re = 3.0 × 105, the suction flow control can make the lift-to-drag ratio of the wing increase by 8.62%, and the aerodynamic characteristics of the wing are improved effectively.

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