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The forces and pressure distribution at subsonic speeds on a cambered and twisted wing having 45 degrees of sweepback and aspect ratio of 3 and a taper ratio of 0.5

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T16:08:35Z
date available2017-09-04T16:08:35Z
date copyright01/01/1952
date issued1952
identifier otherSEMCWDAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/71795
description abstractINTRODUCTION
The use of camber and twist as a means of improving the aerodynamic characteristics of 8wept-back wings with moderately thin airfoil sections has received considerable attention. While some force and pressure data have been obtained showing the effects of camber and twist on the aerodynamic characteristics of swept-back wings at low speeds (e.g., references 1 and 2), the available pressure data at high subsonic Mach numbers are rather limited, particularly for swept-back wings of low aspect ratio.
The results of pressure-distribution and force tests of an unhampered and untwisted wing having the quarter-chord line swept back 450 an aspect ratio of 3.0, and a taper ratio of 0.5 have been reported in reference 3. The results of similar tests of a cambered and twisted wing having the same plan form are presented herein. Both wings were tested in the Ames 12-foot pressure wind tunnel over wide ranges of Reynolds numbers and subsonic mach numbers. The complete pressure distribution data are presented in tabular form. Portions of the data from reference 3 have been included in the present report for purposes of comparison.
languageEnglish
titleNACA-RM-A52D22num
titleThe forces and pressure distribution at subsonic speeds on a cambered and twisted wing having 45 degrees of sweepback and aspect ratio of 3 and a taper ratio of 0.5en
typestandard
page167
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1952
contenttypefulltext


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