NDLI: Characteristics of a configuration with a large angle of sweepback

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Characteristics of a configuration with a large angle of sweepback

Content Provider	NASA Technical Reports Server (NTRS)
Author	Jones, R. T.
Organization	The National Aeronautics and Space Administration (NASA)
Copyright Year	1947
Description	A brief discussion is given of some recent experimental results obtained on a supersonic transport-type airplane for a large range of Mach numbers. The theoretical arguments which led to the configuration of this airplane were brought out at the NACA Conference on Supersonic Aerodynamics at the Langley Laboratory, June 1940, 1947; hence, it will not be necessary to dwell on them herein. Briefly, our calculations showed that a reasonably good lift-drag ratio and, hence, reasonably good fuel economy, could be maintained up to a Mach number of 1.5. The configuration required would incorporate a long slender body and wings having a large angle of sweepback together with the highest practicable aspect ratio.
File Size	292463
File Format	PDF
Alternate Webpage(s)	http://www.archive.org/details/nasa_techdoc_19790079938
Archival Resource Key	ark:/13960/t6sx71d48
Language	English
Publisher Date	1947-01-01
Access Restriction	Open
Subject Keyword	Aerodynamics Supersonic Inlets Wind Tunnel Models Aerodynamic Configurations Fuselages Inlet Pressure Mach Number Pressure Recovery Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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