NACA-TN-3497

Summary of results of a wind-tunnel investigation of nine related horizontal tails

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T15:11:52Z
date available	2017-09-04T15:11:52Z
date copyright	01/01/1955
date issued	1955
identifier other	LVNUYDAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/10296
description abstract	The results of a wind-tunnel investigation of a series of models of nine related horizontal tails have been summarized to provide basic design information; to indicate the effects of aspect ratio, sweepback, and changes in the Mach number; and to provide experimental values of the lift and hinge-moment parameters for comparison with values computed by a method employing lifting-surface theory. The models had aspect ratios from 2 to 6, angles of sweepback of the quarter-chord line from 5.7° to 45°, a taper ratio of 0.5, and had 30-percent-chord, sealed, plain flaps. The Mach number was varied from 0.12 to 0.94 for Reynolds numbers of 2, 3, or 4 million. Also, a constant-chord airfoil having the NACA 64A010 section and completely spanning the wind tunnel was tested at a Mach number of 0.12. This airfoil had the same section and flap-chord ratio as the nine horizontal-tail models.
language	English
title	NACA-TN-3497	num
title	Summary of results of a wind-tunnel investigation of nine related horizontal tails	en
type	standard
page	106
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1955
contenttype	fulltext