Efficiency of plasma actuator ionization in shock wave modification in a rarefied supersonic flow over a flat plate

2014 ◽  
Author(s):  
Romain Joussot ◽  
Viviana Lago ◽  
Jean-Denis Parisse
Keyword(s):  
Shock Wave ◽  
Supersonic Flow ◽  
Flat Plate ◽  
Plasma Actuator

Influence of a plasma actuator on aerodynamic forces over a flat plate interacting with a rarefied Mach 2 flow

2016 ◽  
Vol 26 (7) ◽  
pp. 2081-2100 ◽  
Author(s):  
Sandra Coumar ◽  
Romain Joussot ◽  
Jean Denis Parisse ◽  
Viviana Lago
Keyword(s):  
Shock Wave ◽  
Flat Plate ◽  
Stokes Equations ◽  
Plasma Actuator ◽  
Heating Element ◽  
Aerodynamic Forces ◽  
Heat Management ◽  
Content Type ◽  
Numerical Investigations ◽  
Wave Angle

Purpose The purpose of this paper is to describe experimental and numerical investigations focussed on the shock wave modification induced by a dc glow discharge. The model is a flat plate in a rarefied Mach 2 air flow, equipped with a plasma actuator composed of two electrodes. The natural flow without actuation exhibits a shock wave with a hyperbolic shape. When the discharge is on, the shock wave shape remains hyperbolic but the shock wave is pushed forward, leading to an increase in the shock wave angle. In order to discriminate thermal effects from purely plasma ones, the plasma actuator is then replaced by an heating element. Design/methodology/approach The experimental study is carried out with the super/hypersonic wind tunnel MARHy located at the ICARE Laboratory in Orléans. The experimental configuration with the heating element is simulated with a code using the 2D full compressible Navier-Stokes equations adapted for the rarefied conditions. Findings For heating element temperatures equal to the flat plate wall surface ones with the discharge on, experimental and numerical investigations showed that the shock wave angle was lower with the heating element, only 50 percent of the values got with the plasma actuator, meaning that purely plasma effects must also be considered to fully explain the flow modifications observed. The results obtained with the numerical simulations are then used to calculate the aerodynamic forces, i.e. the drag and the lift. These numerical results are then extrapolated to the plasma actuator case and it was found that the drag coefficient rises up to 13 percent when the plasma actuator is used, compared to only 5 percent with the heating element. Originality/value This paper matters in the topic of atmospheric entries where flow control, heat management and aerodynamic forces are of huge importance.

Experimental Research of Gasdynamic Liquid Drops Breakup in the Supersonic Flow with an Oblique Shock Wave

2020 ◽  
Author(s):  
K. Yu. Arefyev ◽  
O. V. Guskov ◽  
A. N. Prokhorov ◽  
A. S. Saveliev ◽  
E. E. Son ◽  
...  
Keyword(s):  
Shock Wave ◽  
Supersonic Flow ◽  
Experimental Research ◽  
Oblique Shock ◽  
Oblique Shock Wave ◽  
Liquid Drops

Evolution of weak shock wave in two-dimensional steady supersonic flow in dusty gas

2019 ◽  
Vol 160 ◽  
pp. 552-557 ◽  
Author(s):  
Rahul Kumar Chaturvedi ◽  
Pooja Gupta ◽  
L.P. Singh
Keyword(s):  
Shock Wave ◽  
Supersonic Flow ◽  
Weak Shock ◽  
Weak Shock Wave ◽  
Dusty Gas ◽  
Two Dimensional

Flowfield characteristics of a transverse jet into supersonic flow with pseudo-shock wave

Shock Waves ◽  
2012 ◽  
Vol 22 (6) ◽  
pp. 533-545 ◽  
Author(s):  
H. Yamauchi ◽  
B. Choi ◽  
K. Takae ◽  
T. Kouchi ◽  
G. Masuya
Keyword(s):  
Shock Wave ◽  
Supersonic Flow ◽  
Transverse Jet
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