NACA-TN-3030

A method for calculating the subsonic steady-state loading on an airplane with a wing of arbitrary plan form and stiffness

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T15:36:27Z
date available	2017-09-04T15:36:27Z
date copyright	01/01/1953
date issued	1953
identifier other	OSNUYDAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/38456
description abstract	A method for computing the steady-state span load distribution on an elastic airplane wing for specified airplane weights and load factors is given. The method is based on a modification of the Weissinger L-method and applies at sub-critical Mach numbers. It includes the effects of external stores and fuselage on the spanwise loading. Modifications are outlined for treating tail-boom and tailless airplane configurations and for calculating the divergence dynamic pressure of a swept wing with a large external store. A method is also outlined for reducing wind-tunnel data to obtain effective aerodynamic coefficients which are free of model flexibility effects. The effects of Mach number can readily be evaluated from the aerodynamic coefficients thus obtained.
language	English
title	NACA-TN-3030	num
title	A method for calculating the subsonic steady-state loading on an airplane with a wing of arbitrary plan form and stiffness	en
type	standard
page	123
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1953
contenttype	fulltext