Next Article in Journal
Viability of an Electrically Driven Pump-Fed Hybrid Rocket for Small Launcher Upper Stages
Previous Article in Journal
Verification of Boundary Conditions Applied to Active Flow Circulation Control
Article Menu
Issue 3 (March) cover image

Export Article

Open AccessArticle
Aerospace 2019, 6(3), 35; https://doi.org/10.3390/aerospace6030035

Plasma-Assisted Control of Supersonic Flow over a Compression Ramp

1,2,*,†, 1,† and 1,†
1
Department of Aerospace and Mechanical Engineering, University of Notre Dame, Notre Dame, IN 46556, USA
2
Department of Aeronautics and Astronautics, The University of Tokyo, Tokyo 113-8656, Japan
*
Author to whom correspondence should be addressed.
These authors contributed equally to this work.
Received: 13 February 2019 / Revised: 6 March 2019 / Accepted: 7 March 2019 / Published: 12 March 2019
  |  
PDF [7477 KB, uploaded 12 March 2019]
  |  

Abstract

This study considers the effect of an electric discharge on the flow structure near a 19.4° compression ramp in Mach-2 supersonic flow. The experiments were conducted in the supersonic wind tunnel SBR-50 at the University of Notre Dame. The stagnation temperature and pressure were varied in a range of 294–600 K and 1–3 bar, respectively, to attain various Reynolds numbers ranging from 5.3 × 105 to 3.4 × 106 based on the distance between the exit of the Mach-2 nozzle and the leading edge of the ramp. Surface pressure measurements, schlieren visualization, discharge voltage and current measurements, and plasma imaging with a high-speed camera were used to evaluate the plasma control authority on the ramp pressure distribution. The plasma being generated in front of the compression ramp shifted the shock position from the ramp corner to the electrode location, forming a flow separation zone ahead of the ramp. It was found that the pressure on the compression surface reduced almost linearly with the plasma power. The ratio of pressure change to flow stagnation pressure was also an increasing function of the ratio of plasma power to enthalpy flux, indicating that the task-related plasma control effectiveness ranged from 17.5 to 25. View Full-Text
Keywords: plasma-assisted flow control; supersonic airflow; compression ramp plasma-assisted flow control; supersonic airflow; compression ramp
Figures

Graphical abstract

This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited (CC BY 4.0).
SciFeed

Share & Cite This Article

MDPI and ACS Style

Watanabe, Y.; Houpt, A.; Leonov, S.B. Plasma-Assisted Control of Supersonic Flow over a Compression Ramp. Aerospace 2019, 6, 35.

Show more citation formats Show less citations formats

Note that from the first issue of 2016, MDPI journals use article numbers instead of page numbers. See further details here.

Related Articles

Article Metrics

Article Access Statistics

1

Comments

[Return to top]
Aerospace EISSN 2226-4310 Published by MDPI AG, Basel, Switzerland RSS E-Mail Table of Contents Alert
Back to Top