Abstract
When a supersonic jet impinges on an inclined flat surface, a complex flow structure is established due to the interaction between the flat surface and the shock system of the free jet. The main objective of the present research is to enhance the understanding of this complex flow phenomenon at surface inclinations between -5° and 30°. A set of experiments was conducted, using a Ludwieg tube tunnel, which included surface flow visualization and surface pressure measurements. From the results, correlation between surface flow visualization and surface pressure distribution was established. Shock reflections as well as supersonic and subsonic surface flow regions were identified based on the correlation. Additionally, it was found that for inclinations less than 20°. a suction region appeared on the surface between the two major high pressure regions which are in the supersonic flow regime. At surface inclinations higher than 10°, regions of strong boundary layer separation appear behind the upper tail reflected shock. It was also found that minimum and maximum pressure are always on the centerline of the flow.
Original language | English |
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DOIs | |
State | Published - 1995 |
Bibliographical note
Publisher Copyright:© 1995, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved.
ASJC Scopus subject areas
- Energy Engineering and Power Technology
- Electrical and Electronic Engineering
- Mechanical Engineering
- Control and Systems Engineering
- Aerospace Engineering