AERO-THERMAL PERFORMANCE OF A COOLED WINGLET AT ENGINE REPRESENTATIVE MACH AND REYNOLDS NUMBERS
This paper presents an experimental investigation of the aero-thermal performance of a cooled winglet tip, under transonic conditions (exit Mach number of 1.0, and an exit Reynolds number of 1.27×106, based on axial chord). Spatiallyresolved heat transfer data and film cooling effectiveness data are...
| Main Authors: | , , , , , |
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| Format: | Journal article |
| Language: | English |
| Published: |
2012
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