NACA-TN-3848

A study of several factors affecting the stability contributed by a horizontal tail at various vertical positions on a sweptback-wing airplane model

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T17:04:00Z
date available	2017-09-04T17:04:00Z
date copyright	01/01/1956
date issued	1956
identifier other	XYNUYDAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/127593
description abstract	A study was made in the Langley 19-foot pressure tunnel to determine the effects of fuselage afterbody shape , split flaps, and variations in the span of the leading-edge flaps on the stability contributed by the horizontal tail to an airplane with the wing leading edge swept back 42º. Supplementary tests were made to determine some of the characteristics of the air flow In the vicinity of the tail, the wing being equipped with 0.575-span leading-edge flaps and 0.5-span split flaps. All data were obtained at a Reynolds number 6.8 X 10⁶.
language	English
title	NACA-TN-3848	num
title	A study of several factors affecting the stability contributed by a horizontal tail at various vertical positions on a sweptback-wing airplane model	en
type	standard
page	29
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1956
contenttype	fulltext