Publication Date:
2019-06-27
Description:
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.
Keywords:
FLUID MECHANICS
Type:
NASA-TN-D-7635
,
E-7506
Format:
application/pdf
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