NDLI: Subsonic and supersonic longitudinal stability and control characteristics of an aft tail fighter configuration with cambered and uncambered wings and uncambered fuselage

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Subsonic and supersonic longitudinal stability and control characteristics of an aft tail fighter configuration with cambered and uncambered wings and uncambered fuselage

Content Provider	NASA Technical Reports Server (NTRS)
Author	Dollyhigh, S. M.
Copyright Year	1974
Description	An investigation has been made in the Mach number range from 0.20 to 2.16 to determine the longitudinal aerodynamic characteristics of a fighter airplane concept. The configuration concept employs a single fixed geometry inlet, a 50 deg leading-edge-angle clipped-arrow wing, a single large vertical tail, and low horizontal tails. The wing camber surface was optimized in drag due to lift and was designed to be self-trimming at Mach 1.40 and at a lift coefficient of 0.20. An uncambered or flat wing of the same planform and thickness ratio was also tested. However, for the present investigation, the fuselage was not cambered. Further tests should be made on a cambered fuselage version, which attempts to preserve the optimum wing loading on that part of the theoretical wing enclosed by the fuselage.
File Size	16198937
Page Count	99
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19740023306
Archival Resource Key	ark:/13960/t48q0sk4p
Language	English
Publisher Date	1974-08-01
Access Restriction	Open
Subject Keyword	Aerodynamics Flight Characteristics Longitudinal Control Aerodynamic Configurations Wind Tunnel Tests Performance Prediction Fighter Aircraft Longitudinal Stability 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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