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Tests in the Ames 40- by 80-foot wind tunnel of an airplane model with an aspect ratio 4 triangular wing and an all-movable horizontal tail - high-lift devices and lateral controls

contributor authorNASA - National Aeronautics and Space Administration (NASA)
date accessioned2017-09-04T15:57:36Z
date available2017-09-04T15:57:36Z
date copyright01/01/1953
date issued1953
identifier otherBFMCWDAAAAAAAAAA.pdf
identifier urihttps://yse.yabesh.ir/std/handle/yse/60902
description abstractINTRODUCTION
The low-speed aerodynamic characteristics of an airplane model with an aspect ratio 4 triangular wing and an all-movable horizontal tail have been under investigation in the Ames 40- by 80-foot wind tunnel. The longitudinal aerodynamic characteristics of the model at zero sideslip have been reported in reference 1; included therein were data covering the effect of horizontal-tail aspect ratio and vertical location. The results of the tests of reference I indicated that the horizontal tail having the greater aspect ratio (4.4) located in the extended wing-chord plane gave the best stability and the lowest drag; therefore, this tail configuration was used in the present investigation.
Presented herein are the results of tests of the model with high-lift devices, and lateral and directional controls. The high-lift devices included slotted inboard flaps and plain outboard flaps. Three lateral controls were tested; namely, the inboard flaps, the outboard flaps, and the all-movable horizontal tail. In addition, a rudder of constant chord was tested as a directional control device. The data herein are presented without analysis to expedite publication.
languageEnglish
titleNACA-RM-A52K13num
titleTests in the Ames 40- by 80-foot wind tunnel of an airplane model with an aspect ratio 4 triangular wing and an all-movable horizontal tail - high-lift devices and lateral controlsen
typestandard
page46
statusActive
treeNASA - National Aeronautics and Space Administration (NASA):;1953
contenttypefulltext


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