NACA-RM-A8C03

Low-speed investigation of a small triangular wing of aspect ratio 2.0. III - static stability with twin vertical fins

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T18:17:22Z
date available	2017-09-04T18:17:22Z
date copyright	01/01/1948
date issued	1948
identifier other	HPCTUDAAAAAAAAAA.pdf
identifier uri	http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/200232
description abstract	INTRODUCTION Previous tests of a single vertical tall in combination with an approximately triangular wing (reference1, configurations 7 and 8) have shown marked losses in directional stability at high lift coefficients. Considerations of the flow about triangular wings at high lift coefficients (as discussed in references 2 and 3) indicated that vertical fins mounted outboard of the center line of the wing would possibly provide more desirable characteristics. In order to check the merits of outboard vertical fins, a short investigation of twin vertical fins on a triangular wing was made in the Ames 7- by 10-foot wind tunnel. The characteristics of the model with fins mounted symmetrically about the wing-chord plane and fins mounted wholly above the wing-chord plane were investigated.
language	English
title	NACA-RM-A8C03	num
title	Low-speed investigation of a small triangular wing of aspect ratio 2.0. III - static stability with twin vertical fins	en
type	standard
page	13
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1948
contenttype	fulltext