NACA-TR-631

Airfoil section characteristics as applied to the prediction of air forces and their distribution on wings

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T16:14:22Z
date available	2017-09-04T16:14:22Z
date copyright	01/01/1938
date issued	1938
identifier other	STWUYDAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/77603
description abstract	The results of previous reports dealing with airfoil section characteristics and span load distribution data are coordinated into a method for determining the air forces and their distribution on airplane wings. Formulas are given from which the resultant force distribution may be combined to find the wing aerodynamic center and pitching moment. The force distribution may also be resolved to determine the distribution of chord and beam components. The forces are resolved in such a manner that it is unnecessary to take the induced drag into account. An illustration of the method is given for a monoplane and a biplane for the conditions of steady flight and a sharp-edge gust. The force determination is completed by outlining a procedure for finding the distribution of load along the chord of airfoil sections.
language	English
title	NACA-TR-631	num
title	Airfoil section characteristics as applied to the prediction of air forces and their distribution on wings	en
type	standard
page	36
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1938
contenttype	fulltext