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Low-subsonic investigation to determine the chordwise pressure distribution and effectiveness of spoilers on a thin, low-aspect-ratio, unswept, untapered, semispan wing and on the wing with leading and trailing-edge flaps

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T17:52:52Z
date available2017-09-04T17:52:52Z
date copyright01/01/1958
date issued1958
identifier otherFCYIYDAAAAAAAAAA.pdf
identifier urihttp://yse.yabesh.ir/std/handle/yse/176019
description abstractINTRODUCTION
Considerable interest has been shown in the use of spoilers for lateral control and gust alleviation. The spoiler is more effective as a lateral control when it is located in a more rearward position, and, as pointed out in references 1 and 2, the spoiler is more effective as a gust alleviator (reduces the lift-curve slope) when it is located in a more forward position.
The present investigation was made in the Langley 300-MPH 7- by 10-foot tunnel to obtain the static longitudinal and lateral aerodynamic characteristics and the chordwise pressure distribution at the 60-percentsemispan station over a thin, low-aspect-ratio, unswept, untapered, semispan wing with a 10-percent-chord projection spoiler of various spans located at various chordwise locations on the wing with leading- and trailing-edge flaps.
The results of the investigation are presented without discussion. Pressure coefficients, section normal-force coefficients, and section pitching-moment coefficients are presented in tabular form.
languageEnglish
titleNACA-RM-L58B05num
titleLow-subsonic investigation to determine the chordwise pressure distribution and effectiveness of spoilers on a thin, low-aspect-ratio, unswept, untapered, semispan wing and on the wing with leading and trailing-edge flapsen
typestandard
page134
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1958
contenttypefulltext


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