NACA-TN-1813

A study of flow changes associated with airfoil section drag rise at supercritical speeds

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T16:04:57Z
date available	2017-09-04T16:04:57Z
date copyright	01/01/1949
date issued	1949
identifier other	RUONEEAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/68166
description abstract	A study of experimental pressure distributions and sections was made. A correlation appears to exist between the drag-divergence Mach number and the free-stream Mach number and the free-stream Mach number for which sonic velocity occurs at the airfoil crest, the chordwise station at which the airfoil surface is tangent to the free-stream direction. it was found that, since the Mach number for which sonic velocity occurs at the airfoil crest can be estimated satisfactorily by means of the Prandtl-Glauert rule, a method is provided whereby the drag-divergence Mach number of an airfoil section at a given angle of attack can be estimated from the low-speed pressure distribution and the airfoil profile This method was used to predict with a reasonable degree of accuracy the drag-divergence Mach number of a considerable number of airfoil sections having diverse shapes and a wide range of thickness-chord ratios.
language	English
title	NACA-TN-1813	num
title	A study of flow changes associated with airfoil section drag rise at supercritical speeds	en
type	standard
page	32
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1949
contenttype	fulltext