NASA NTRS · 19740011799
Differential analysis for the turbulent boundary layer on a compressor blade element (including boundary-layer separation)
Abstract
A two-dimensional differential analysis is developed to approximate the turbulent boundary layer on a compressor blade element with strong adverse pressure gradients, including the separated region with reverse flow. The predicted turbulent boundary layer thicknesses and velocity profiles are in good agreement with experimental data for a cascade blade, even in the separated region.
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Schmidt, J. F., Todd, C. A.. 1974-04-01. Differential analysis for the turbulent boundary layer on a compressor blade element (including boundary-layer separation). https://ntrs.nasa.gov/citations/19740011799
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