NACA-TN-1854

APPROXIMATE CORRECTIONS FOR THE EFFECTS OF COMPRESSIBILITY ON THE SUBSONIC STABILITY DERIVATIVES OF SWEPT WINGS

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T15:29:31Z
date available	2017-09-04T15:29:31Z
date copyright	04/01/1949
date issued	1949
identifier other	NXWIWEAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/30786
description abstract	SUMMARY A method which has previously been presented for the estimation of the low-speed stability derivatives of swept wings is modified "by means of the Prandtl-Glauert rule to yield approximate corrections for the first-order three-dimensional effects of compressible flow in the subsonic region. Corrections are presented in chart form for several aspect ratios and angles of sweep and may he computed rather simply for other aspect ratios and angles of sweep. Lift-curve slopes and values of damping in roll are compared with those obtained by use of a generally accepted method and are discussed in relation to unpublished data.
language	English
title	NACA-TN-1854	num
title	APPROXIMATE CORRECTIONS FOR THE EFFECTS OF COMPRESSIBILITY ON THE SUBSONIC STABILITY DERIVATIVES OF SWEPT WINGS	en
type	standard
page	36
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1949
contenttype	fulltext