NDLI: Investigation of the effects of twist and camber on the aerodynamic characteristics of a 50 degrees 38 minutes sweptback wing of aspect ratio 2.98 : transonic-bump method

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Investigation of the effects of twist and camber on the aerodynamic characteristics of a 50 degrees 38 minutes sweptback wing of aspect ratio 2.98 : transonic-bump method

Content Provider	NASA Technical Reports Server (NTRS)
Copyright Year	1951
Description	An investigation of two semispan wings swept back 50 degrees 38 minutes was conducted in the Langley high-speed 7- by 10-foot tunnel over a Mach number range of 0.68 to 1.15 by use of the transonic-bump technique. This paper presents the results of the investigation of wing-alone and wing-fuselage configurations of the two wings; one was an untwisted uncambered wing and the other was the same wing but incorporated twist and camber designed to give uniform load at a lift coefficient of 0.25 at a Mach number of 1.10. The semispan wings had their quarter-chord lines swept back 50 degrees 38 minutes, aspect ratios 2.98, taper ratios 0.45, and modified NACA 64A-series airfoil sections tapered in thickness. Lift, pitching moment, drag, and bending moment were obtained for these configurations.
File Size	13251665
Page Count	31
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19930086543
Archival Resource Key	ark:/13960/t25b4fn93
Language	English
Publisher Date	1951-08-27
Access Restriction	Open
Subject Keyword	Wings, Complete - Design Variables Stability, Longitudinal - Static Wings, Complete - Sweep Mach Number Effects - Complete Wings Wing-fuselage Combinations - Airplanes Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Technical Report

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