What is it about?
Shocks and shock-induced boundary layer separation occur in a supersonic flow over a flexible intake, also known as a compression ramp, of a scramjet or ramjet engine. This work details the simulation of such supersonic flows together with elastodynamics of the flexible compression ramp. We also show the nature of the shock structure over the compression ramp with and without flexibility and inertia of the compression ramp.
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Photo by Timothy Holmes on Unsplash
Why is it important?
Intakes form the basis of supersonic ramjets and hypersonic scramjets. They decelerate and compress the flow before it enters the combustion chamber. Compression ramps, depending on the Mach number, Reynolds number, and ramp angle, can lead to boundary layer separation, shock formation, and shock-boundary layer interaction. Flexibility and inertia of the compression layer may change the shock structure and pressure compression ratio as well as cause aeroelastic instabilities such as flutter.
Perspectives
This research shows that flexibility and inertia of the compression corner can change the shock structure and pressure ratio of the flow over it. This in turn could lead to a phenomenon known as unstart of the ramjet or scramjet engine.
Kartik Venkatraman
Indian Institute of Science
Read the Original
This page is a summary of: Shock boundary layer interactions in a supersonic flow over a flexible compression ramp, June 2022, American Institute of Aeronautics and Astronautics (AIAA),
DOI: 10.2514/6.2022-4049.
You can read the full text:
Resources
Shock boundary layer interactions in a supersonic flow over a flexible compression ramp
The link takes one to the online presentation made at the 2022 AIAA Aviation Forum.
Shadow graph
Shadow graph of numerical simulation of supersonic flow over 25 deg compression ramp.
Streamlines
Streamlines with pressure contours of supersonic flow over a 25 deg flexible compression ramp.
Contributors
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