NACA-TR-1071

Theoretical symmetric span loading due to flap deflection for wings of arbitrary plan form at subsonic speeds

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T16:25:17Z
date available	2017-09-04T16:25:17Z
date copyright	01/01/1952
date issued	1952
identifier other	TXDZYDAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/88481
description abstract	A simplified lifting-surface theory is applied to the problem of evaluating span loading due to flap deflection for arbitrary wing plan forms. With the resulting procedure, the effects of flap deflection on the span loading and associated aerodynamic characteristics can be easily computed for any wing which is symmetrical about the root chord and which has a straight quarter-chord line over the wing semispan. The effects of compressibility and spanwise variation of section lift-curve slope are taken into account by the procedure. The method presented can also be used to calculate the downwash in the vertical center of the wake of a wing which has arbitrary spanwise loading.
language	English
title	NACA-TR-1071	num
title	Theoretical symmetric span loading due to flap deflection for wings of arbitrary plan form at subsonic speeds	en
type	standard
page	41
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1952
contenttype	fulltext