Integrated airframe-nozzle performance for designing twin-engine fighters

Glasgow, E. R.

doi:10.2514/6.1973-1303

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1973

1990

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Cited by 7 publications

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“…The afterbodies of these models comprised from 20 to 25 percent of the total model length, but produced 38 to 50 percent of the total aircraft drag. Up to half of this afterbody drag results from adverse interference in the afterbody region and pressure drag on the afterbody (3)(4)(5)(6)(7)(8)(9).…”

Section: Discussionmentioning

confidence: 99%

Airframe/Propulsion Integration at Transonic Speeds

Henderson

1990

Volume 2: Aircraft Engine; Marine; Microturbines and Small Turbomachinery

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A significant level of research is ongoing at NASA’s Langley Research center on integrating the propulsion system with the aircraft. This program has included nacelle/pylon/wing integration for turbofan transports, propeller/nacelle/wing integration for turboprop transports, and nozzle/afterbody/empennage integration for high performance aircraft. The studies included in this paper focus more specifically on pylon shaping and nacelle bypass ratio studies for turbofan transports, nacelle and wing contouring and propeller location effects for turboprop transports, empennage effects, and thrust vectoring for high performance aircraft. The studies were primarily conducted in NASA Langley’s 16-Foot Transonic Tunnel at Mach numbers up to 1.20.

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