Journal
JOURNAL OF PROPULSION AND POWER
Volume 24, Issue 6, Pages 1168-1181Publisher
AMER INST AERONAUT ASTRONAUT
DOI: 10.2514/1.24585
Keywords
-
Categories
Funding
- European Office of Aerospace Research and Development
- program 20 of the Presidium of the Russian Academy of Sciences
Ask authors/readers for more resources
The results of experimental and numerical investigations of the interaction between the near-wall electrical discharge and supersonic airflow in an aerodynamic channel with constant and variable cross sections are presented. Peculiar properties of the surface quasi-direct-current discharge generation in the flow are described. The mode with flow separation developing outside the discharge region is revealed as a specific feature of such a configuration. An interaction model is proposed on the basis of measurements and observations. A regime of gas-dynamic screening of a mechanical obstacle installed on the channel wall is studied. Variation of the main flow parameters caused by the surface discharge is quantified. The ability of the discharge to shift an oblique shock in an inlet is demonstrated experimentally. The influence of relaxation processes in nonequilibrium excited gas on the flow structure is analyzed. Comparison of the experimental data with the results of calculations based on the analytical model and on numerical simulations is presented.
Authors
I am an author on this paper
Click your name to claim this paper and add it to your profile.
Reviews
Recommended
No Data Available