| Issue |
Volume 3, 2012
Progress in Flight Physics
|
|
|---|---|---|
| Page(s) | 557 - 568 | |
| Section | Chapter Six. Flow Control | |
| DOI | https://doi.org/10.1051/eucass/201203557 | |
| Published online | 29 January 2013 | |
Flow control in a supersonic inlet model by electrical discharge
1
Joint Institute for High Temperature Russian Academy of Sciences Moscow, Russia
2
MBDA-France France
This paper reports the results of experimental work on supersonic Flow Control by Weakly-Ionized Plasma. Particular objective of this activity is to demonstrate the steering effect of near-surface electrical discharge on supersonic flow structure in a model two-dimensional (2D) aerodynamic con¦guration with three-shock compression ramp. The experiments were arranged in lab-scale facility PWT-50 of JIHT RAS at connected pipe flow pattern. At rather sophisticated character of plasma-flow interaction, such a technique can be considered as a feasible method for accurate control of shocks position and angle in supersonic inlet.
© Owned by the authors, published by EDP Sciences, 2012