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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)
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.
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.
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| contributor author | NASA - National Aeronautics and Space Administration (NASA) | |
| date accessioned | 2017-09-04T18:46:07Z | |
| date available | 2017-09-04T18:46:07Z | |
| date copyright | 01/01/1952 | |
| date issued | 1952 | |
| identifier other | AMSWXDAAAAAAAAAA.pdf | |
| identifier uri | http://yse.yabesh.ir/std;jsessionid=3826AF679D40527318548F1EFDEC014A/handle/yse/227384 | |
| description 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. | |
| language | English | |
| title | NACA-RM-L52B15 | num |
| title | 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) | en |
| type | standard | |
| page | 60 | |
| status | Active | |
| tree | NASA - National Aeronautics and Space Administration (NASA):;1952 | |
| contenttype | fulltext |