Interference Effects of Very High Bypass Ratio Nacelle Installations on a Low-Wing Transport

[+] Author and Article Information
A. M. Ingraldi, R. J. Re, O. C. Pendergraft

NASA Langley Research Center, Hampton, VA 23681

T. T. Kariya

Vigyan Research Associates, Inc., Hampton, VA 23666

J. Eng. Gas Turbines Power 114(4), 809-815 (Oct 01, 1992) (7 pages) doi:10.1115/1.2906661 History: Received March 04, 1991; Online April 24, 2008


A twin-engine, low-wing transport model, with a supercritical wing designed for a cruise Mach number of0.77 and a lift coefficient of 0.55, was tested in the 16-Foot Transonic Tunnel at NASA Langley Research Center. The purpose of this test was to compare the wing/nacelle interference effects of superfans (very high bypass ratio turbofans, BPR ≈ 18) with the interference effects of advanced turbofans (BPR ≈ 6). Flow-through nacelles were used in this study. Forces and moments on the complete model were measured using a strain gage balance and extensive surface static pressure measuements (383 orifice locations) were made on the model’s wing, nacelles, and pylons. Data were taken at Mach numbers from 0.50 to 0.80 and model angle-of-attack was varied from −4 to +8 deg. Results of the investigation indicate that superfan nacelles can be installed with approximately the same drag penalty as conventional turbofan nacelles.

Copyright © 1992 by The American Society of Mechanical Engineers
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