NACA-TN-4040

Estimation of incremental pitching moments due to trailing-edge flaps on swept and triangular wings

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T17:13:58Z
date available	2017-09-04T17:13:58Z
date copyright	01/01/1957
date issued	1957
identifier other	YZNUYDAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/137448
description abstract	A method is presented whereby incremental pitching moments can be estimated for swept and triangular wings having arbitrary types of trailing-edge high-lift flaps. In the method use is made of span-loading theory together with two-dimensional airfoil data adjusted for the effects of sweep. The method as presented was limited to low speeds and small angles of attack. Application of the method is demonstrated for some 58 cases covering various types of flaps on wings having a wide range of sweep, aspect ratio, and taper ratio. For all wings, swept as well as triangular, a mean derivation from experiment of about 0.02 in incremental pitching-moment coefficient was found.
language	English
title	NACA-TN-4040	num
title	Estimation of incremental pitching moments due to trailing-edge flaps on swept and triangular wings	en
type	standard
page	32
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1957
contenttype	fulltext