Effect of reduced aft diameter and increased blade number on high-speed counterrotation propeller performance

Performance data of 0.17-scale model counterrotation pusher propeller configurations were taken in the NASA Lewis 8- by 6-Foot Supersonic Wind Tunnel at Mach numbers of 0.66, 0.71, 0.75, and 0.79. These tests investigated the aerodynamic performance of the unducted fan (UDF) demonstrator propeller e...

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Bibliographische Detailangaben

Hauptverfasser:	Rose, Gayle E., Jeracki, Robert J.
Format:	Tagungsbericht
Sprache:	eng
Schlagworte:	Aerodynamics
Online-Zugang:	Volltext bestellen
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