The design and test of forecowl profiles for a podded engine nacelle of modern proportions, with the specific aim of obtaining favorable supercritical flow development over the cowl exterior is described. Six cowl shapes were tested, exploiting the pressure distribution principle previously evolved for high speed airfoils. Features of the measured surface pressure distributions over the cowls were related to the occurrence of drag rise, from either increase of Mach number or decrease of flow ratio (spillage). The level of high speed drag performance reached by the best cowl designs tested was equivalent to or slightly better than the corresponding optimum NACA 1-series cowl, superiority at low speed being retained throughout.
The Design of Axisymmetric Cowls for Podded Nacelles for High by-Pass Ratio Turbofan Engines
1979
81 pages
Report
No indication
English
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