Abstract
The effect of distributed tangential injection of heavy SF6 gas into the wall zone of a boundary layer on the supersonic flow stability and laminar-turbulent transition is experimentally and theoretically investigated at the freestream Mach number M∞ = 2. For the first time it is experimentally shown that in the case of this injection laminar-turbulent transition is downstream displaced.
Original language | English |
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Pages (from-to) | 769-776 |
Number of pages | 8 |
Journal | Fluid Dynamics |
Volume | 52 |
Issue number | 6 |
DOIs | |
Publication status | Published - 1 Nov 2017 |
Externally published | Yes |
Keywords
- compressible boundary layer
- hydrodynamic stability
- injection
- laminar-turbulent transition
- permeable surface
- PERMEABILITY
- STABILITY
- ROUGHNESS