NDLI: Supersonic aerodynamic characteristics of canard, tailless, and aft-tail configurations for 2 wing planforms

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Supersonic aerodynamic characteristics of canard, tailless, and aft-tail configurations for 2 wing planforms

Content Provider	NASA Technical Reports Server (NTRS)
Author	Covell, P. F.
Copyright Year	1985
Description	Aerodynamic characteristics of canard, tailless, and aft tail configurations were compared in tests on a general research model (generic fuselage without canopy, inlets, or vertical tails) at Mach 1.60 and 2.00 in the Langley Unitary Plan Wind Tunnel. Two uncambered wing planforms (trapezoidal with 44 deg leading edge sweep and delta with 60 deg leading edge sweep) were tested for each configuration. The relative merits of the configurations were also determined theoretically, to evaluate the capabilities of a linear theory code for such analyses. The canard and aft tail configurations have similar measured values for lift curve slope, maximum lift drag ratio, and zero lift drag. The stability decrease as Mach number increases is greatest for the tailless configuration and least for the canard configuration. Because of very limited accuracy in predicting the aerodynamic parameter increments between configurations, the linear theory code is not adequate for determining the relative merits of canard, tailless, and aft tail configurations.
File Size	4002444
Page Count	76
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19850019510
Archival Resource Key	ark:/13960/t01z92x60
Language	English
Publisher Date	1985-06-01
Access Restriction	Open
Subject Keyword	Aerodynamics Strakes Aerodynamic Configurations Supersonic Speed Canard Configurations Lift Drag Ratio Wing Planforms Wind Tunnel Tests Body-wing and Tail Configurations Aerodynamic Coefficients Lift 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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