Investigation of laminar-turbulent transition of supersonic boundary layer by scanning constant temperature hot-wire anemometer
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http://aip.scitation.org/doi/pdf/10.1063/1.5065315
Reference10 articles.
1. The Hot-Wire Anemometer in Supersonic Flow
2. Experimental determination of the free-stream disturbance field in a short-duration supersonic wind tunnel
3. Constant temperature hot-wire measurements in a short duration supersonic wind tunnel
4. Turbulence in Supersonic Flow
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