On the Use of Reynolds Number as the Scaling Parameter for the Performance of Plasma Actuator in a Weakly Compressible Flow

2006 ◽  
Author(s):  
Asad Asghar ◽  
Eric Jumper ◽  
Thomas Corke
Keyword(s):  
Reynolds Number ◽  
Compressible Flow ◽  
Plasma Actuator ◽  
Scaling Parameter ◽  
Weakly Compressible

Stability of the Low Reynolds Number Compressible Flow Past a NACA0012 Airfoil

AIAA Journal ◽  
2021 ◽  
pp. 1-15
Author(s):  
Laura Victoria Rolandi ◽  
Thierry Jardin ◽  
Jérôme Fontane ◽  
Jérémie Gressier ◽  
Laurent Joly
Keyword(s):  
Reynolds Number ◽  
Compressible Flow ◽  
Low Reynolds Number ◽  
Naca0012 Airfoil ◽  
Flow Past ◽  
Low Reynolds

S0550204 LES of turbulent-separated flow controlled by DBD plasma actuator at high Reynolds number

2014 ◽  
Vol 2014 (0) ◽  
pp. _S0550204--_S0550204-
Author(s):  
Makoto SATO ◽  
Kengo ASADA ◽  
Taku NONOMURA ◽  
Hikaru AONO ◽  
Aiko YAKENO ◽  
...  
Keyword(s):  
Reynolds Number ◽  
High Reynolds Number ◽  
Separated Flow ◽  
Plasma Actuator ◽  
Dbd Plasma ◽  
High Reynolds ◽  
Turbulent Separated Flow

scholarly journals Adaptive wavelet simulation of weakly compressible flow in a channel with a suddenly expanded section

2016 ◽  
Vol 53 ◽  
pp. 38-48 ◽  
Author(s):  
Naoya Okamoto ◽  
Margarete Oliveira Domingues ◽  
Katsunori Yoshimatsu ◽  
Kai Schneider
Keyword(s):  
Compressible Flow ◽  
Adaptive Wavelet ◽  
Weakly Compressible

Lift Augmentation between Passive and Active Vortex Generator

2016 ◽  
Vol 851 ◽  
pp. 532-537
Author(s):  
Nur Faraihan Zulkefli ◽  
Zulhilmy Sahwee ◽  
Nurhayati Mohd Nur ◽  
Muhamad Nor Ashraf Mohd Fazil ◽  
Muaz Mohd Shukri
Keyword(s):  
Reynolds Number ◽  
Lift Coefficient ◽  
Vortex Generator ◽  
Leading Edge ◽  
Plasma Actuator ◽  
Triangular Shape ◽  
Subsonic Wind Tunnel ◽  
Different Types ◽  
Drag Ratio ◽  
Lift To Drag Ratio

This study was conducted to investigate the performance of passive and active vortex generator on the wing’s flap. The triangular shape of passive vortex generator (VG) was developed and attached on the wing’s flap leading edge while the plasma actuator performed as active vortex generator. The test was carried out experimentally using subsonic wind tunnel with 300 angles extended flap. Three different types of turbulent flow; with Reynolds number 1.5 x105, 2.0 x105, and 2.6x105 were used to study the aerodynamics forces of airfoil with plasma actuator OFF. All Reynolds number used were below 1x106. The result indicated that airfoil with plasma actuator produced higher lift coefficient 12% and lift-to-drag ratio 5% compared to airfoil with passive vortex generator. The overall result showed that airfoil with plasma actuator produced better lift forces compared to passive vortex generator.

DBD Plasma Actuator Multi-Objective Design Optimization at Reynolds Number 63,000: Baseline Case

2013 ◽  
Author(s):  
Taufik Sulaiman ◽  
Satoshi Sekimoto ◽  
Tomoaki Tatsukawa ◽  
Taku Nonomura ◽  
Akira Oyama ◽  
...  
Keyword(s):  
Reynolds Number ◽  
Design Optimization ◽  
Linear Trend ◽  
Lift Coefficient ◽  
Optimization Method ◽  
Input Power ◽  
Plasma Actuator ◽  
Dbd Plasma ◽  
Multi Objective ◽  
Design Variables

The working parameters of the dielectric barrier discharge (DBD) plasma actuator were optimized to gain an understanding of the flow control mechanism. Experiments were conducted at a Reynolds number of 63,000 using a NACA 0015 airfoil which was fixed to the stall angle of 12 degrees. The two objective functions are: 1) power consumption (P) and 2) lift coefficient (Cl). The goal of the optimization is to decrease P while maximizing Cl. The design variables consist of input power parameters. The algorithm was run for 10 generations with a total population of 260 solutions. Although the number of generations and population size was limited due to experimental constraints, the algorithm was able to converge and the approximate Pareto-front was obtained. From the objective function space, we observe a relatively linear trend where Cl increases with P and after a certain threshold, the value of Cl seems to saturate. We discuss the results obtained in the objective space in addition to scatter plot matrix and color maps. This article, with its experiment-based approach, demonstrates the robustness of a Multi-Objective Design Optimization method and its feasibility for wind tunnel experiments.

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