NACA-RM-L9C23

High-subsonic damping-in-roll characteristics of a wing with the quarter-chord line swept back 35 degrees and with aspect ratio 3 and taper ratio 0.6

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T15:07:39Z
date available	2017-09-04T15:07:39Z
date copyright	01/01/1949
date issued	1949
identifier other	LISWXDAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/5449
description abstract	INTRODUCTION An extensive investigation of the effects of compressibility on the damping-in-roll characteristics of various wing plan forms is being conducted in the Langley high-speed 7-by 10-foot tunnel. The 35° swept-back wing of aspect ratio 3 and taper ratio 0.6 employed in the present investigation was that used in the high-speed wind-tunnel investigation of the tailless model reported in reference 1. The present investigation was carried out on a free-rotating apparatus with the purpose of determining the effects of compressibility and angle of attack on the damping-in-doll characteristics of the wing, with and without the vertical fins that were used on the tailless model reported in reference 1.
language	English
title	NACA-RM-L9C23	num
title	High-subsonic damping-in-roll characteristics of a wing with the quarter-chord line swept back 35 degrees and with aspect ratio 3 and taper ratio 0.6	en
type	standard
page	22
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1949
contenttype	fulltext