NDLI: A supersonic through-flow fan engine airframe integration study

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A supersonic through-flow fan engine airframe integration study

Content Provider	NASA Technical Reports Server (NTRS)
Author	Barnhart, Paul J.
Copyright Year	1989
Description	Engine airframe integration effects are investigated for supersonic through-flow fan engines installed on a Mach 3.20 supersonic cruise vehicle. Six different supersonic through-flow fan engine installations covering the effects of engine size, nacelle contour, nacelle placement, and approximate bypass plume effects are presented. The different supersonic through-flow fan installations are compared with a conventional turbine bypass engine configuration on the same basic airframe. The supersonic through-flow fan engine integrations are shown to be comparable to the turbine bypass engine configuration on the basis of installed nacelle wave drag. The supersonic through-flow fan engine airframe integrated vehicles have superior aerodynamic performance on the basis of maximum lift-to-drag ratio than the turbine bypass engine installation over the entire operating Mach number range from 1.10 to 3.20. When approximate bypass plume modeling is included, the supersonic through-flow fan engine configuration shows even larger improvements over the turbine bypass engine configuration.
File Size	745619
Page Count	14
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19900000688
Archival Resource Key	ark:/13960/t87h6gw8x
Language	English
Publisher Date	1989-09-01
Access Restriction	Open
Subject Keyword	Aerodynamics Supersonic Aircraft Aerodynamic Configurations Engine Design Bypass Ratio Airframes Lift Drag Ratio Supersonic Cruise Aircraft Research Engine Airframe Integration Nacelles Aircraft Engines Aircraft Configurations Plumes Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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