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NACA-RM-L52B15

Low-speed lateral-control characteristics of an unswept wing with hexagonal airfoil sections and aspect ratio 2.5 equipped with spoilers and with sharp- and thickened-trailing-edge flap-type ailerons at a Reynolds number of 7.6 x 10(exp 6)

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NASA - National Aeronautics and Space Administration (NASA)
Year: 1952

Abstract: INTRODUCTION
In order to minimize drag at supersonic speeds, thin wings of low aspect ratio and relatively sharp leading edges have been proposed. A tapered wing of this type with an aspect ratio of 2.5 and thin hexagonal airfoil-sections was investigated at low speed in the Langley 19-foot pressure tunnel. The results of the lateral-control investigation of the wing equipped with 0.75-semispan and 0.40-semispan flap-type and spoiler ailerons are the subject of the present paper.
The lateral-control characteristics were determined for the ailerons with several combinations of fuselage, droop-nose flap, and trailing-edge flaps. Inasmuch as the results of references 1 and 2 have indicated that improvements can be made in the rolling effectiveness of flap-type ailerons at transonic and supersonic speeds by thickening the trailing edges, the lateral-control characteristics of the 0.40-semispan aileron were also investigated on the wing with the trailing edge modified to three different thicknesses. In addition, the tests included measurements of-the instantaneous pressure differential between the upper and lower surfaces at four spanwise stations.
URI: http://yse.yabesh.ir/std;query=autho470393FD081DAC426159DD6EFDEC0/handle/yse/227384
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    NACA-RM-L52B15

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contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T18:46:07Z
date available2017-09-04T18:46:07Z
date copyright01/01/1952
date issued1952
identifier otherAMSWXDAAAAAAAAAA.pdf
identifier urihttp://yse.yabesh.ir/std;query=autho470393FD081DAC426159DD6EFDEC0/handle/yse/227384
description abstractINTRODUCTION
In order to minimize drag at supersonic speeds, thin wings of low aspect ratio and relatively sharp leading edges have been proposed. A tapered wing of this type with an aspect ratio of 2.5 and thin hexagonal airfoil-sections was investigated at low speed in the Langley 19-foot pressure tunnel. The results of the lateral-control investigation of the wing equipped with 0.75-semispan and 0.40-semispan flap-type and spoiler ailerons are the subject of the present paper.
The lateral-control characteristics were determined for the ailerons with several combinations of fuselage, droop-nose flap, and trailing-edge flaps. Inasmuch as the results of references 1 and 2 have indicated that improvements can be made in the rolling effectiveness of flap-type ailerons at transonic and supersonic speeds by thickening the trailing edges, the lateral-control characteristics of the 0.40-semispan aileron were also investigated on the wing with the trailing edge modified to three different thicknesses. In addition, the tests included measurements of-the instantaneous pressure differential between the upper and lower surfaces at four spanwise stations.
languageEnglish
titleNACA-RM-L52B15num
titleLow-speed lateral-control characteristics of an unswept wing with hexagonal airfoil sections and aspect ratio 2.5 equipped with spoilers and with sharp- and thickened-trailing-edge flap-type ailerons at a Reynolds number of 7.6 x 10(exp 6)en
typestandard
page60
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1952
contenttypefulltext
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DSpace software copyright © 2017-2020  DuraSpace
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