Comparison of NASA 9×15 Low Speed Wind Tunnel Counter Rotating Open Rotor Data with GE-Anechoic Facility Historic Data for Baseline F31A31 Blade Design

摘要

NASA conducted a program to test scale model open rotor counter-rotating fan blade designs for acoustic and aerodynamic performance. This program, in a collaborative partnership with GE Aviation, includes testing a baseline and many advanced blade designs at NASA Glenn Research Center's 9×15 Low Speed Wind Tunnel (LSWT) using a refurbished model simulator. The baseline blade-set is a remanufacture of the historic F31A31 blade design and is representative of the technology at the end of the earlier 1980's un-ducted counter-rotating fan program at GE Aviation. This paper compares the acoustic and aerodynamic performance of this baseline blade design measured at 9×15 LSWT, at simulated aircraft takeoff/approach conditions, with historic results of the same blade design measured at GE's Anechoic Cell-41 facility in late 1980's As the baseline data measured in 9×15 LSWT will be used to measure the progress made with new advanced blade designs, the comparison of this paper with the historic baseline data would provide a bench mark relative to the 1980's status.