NACA-TN-2151

Estimation of the damping in roll of supersonic-leading-edge wing-body combinations

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T16:39:05Z
date available	2017-09-04T16:39:05Z
date copyright	01/01/1950
date issued	1950
identifier other	VKBUYDAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/102696
description abstract	A description is given of a linear-theory method for the estimation of the damping in roll of supersonic-leading-edge wings mounted on cylindrical bodies. The error resulting from an approximation essential to the method is shown to be small. The damping in roll is calculated for configurations having rectangular and triangular wings; for most of the range of variables the net effect of the body is to decrease the damping in roll.. The body effect is small for body diameters less than about 30 percent of the wing span but increases rapidly with body size above this value.
language	English
title	NACA-TN-2151	num
title	Estimation of the damping in roll of supersonic-leading-edge wing-body combinations	en
type	standard
page	22
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1950
contenttype	fulltext
subject keywords	BODIES
subject keywords	COMBINATIONS
subject keywords	DAMPING
subject keywords	DELTA
subject keywords	FLOW
subject keywords	FUSELAGE
subject keywords	INTERFERENCE
subject keywords	LINEAR
subject keywords	RECTANGULAR
subject keywords	ROLL
subject keywords	SUPERSONIC
subject keywords	THEORIES
subject keywords	WING
subject keywords	WINGS