1992•NASA Technical Reports Server (NASA)Requires access
Installation Effects of Wing-Mounted Turbofan Nacelle-Pylons on a 1/17-Scale, Twin-Engine, Low-Wing Transport Model
Jr Odis C. Pendergraft, Mohanasundaram Anthony, J. Richard, T Kariya Timmy
Open publisher page 6 citations
Abstract
A twin-engine, low-wing transport model, with a supercritical wing of aspect ratio 10.8 designed for a cruise Mach number of 0.77 and a lift coefficient of 0.55, was tested in the Langley 16-Foot Transonic Tunnel. The purpose of this test was to compare the wing-nacelle interference effects of flow-through nacelles simulating superfan engines (very high bypass ratio (BPR ~ 18) turbofan engines) with the wing-nacelle interference effects of current-technology turbofan engines (BPR ~ 6). Forces and moments on the complete model were measured with a strain-gage balance, and extensive external static-pressure measurements (383 orifice locations) were made on the wing, nacelles, and pylons of the model. Data were taken at Mach numbers from 0.50 to 0.80 and at model angles of attack from -4 degrees to 8 degrees. Test results indicate that flow-through nacelles with a very high bypass ratio can be installed on a low-wing transport model with a lower installation drag penalty than for a conventional turbofan nacelle at a design cruise Mach number of 0.77 and lift coefficient of 0.55.