NACA-TN-2960

Drag of circular cylinders for a wide range of Reynolds numbers and Mach numbers

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T17:58:48Z
date available	2017-09-04T17:58:48Z
date copyright	01/01/1953
date issued	1953
identifier other	FSNUYDAAAAAAAAAA.pdf
identifier uri	http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/181943
description abstract	Pressure distributions around circular cylinders placed perpendicular to the stream for subsonic and supersonic flow conditions have been obtained. Drag coefficients calculated from these wind-tunnel tests and from transonic free-flight tests are presented. Drag data are presented for the Mach number range of 0.3 to 2.9. The Reynolds numbers for the subsonic and supersonic Mach numbers were within the ranges of approximately 50,000 to 160,000 and 100,000 to 1,000,000, respectively. No effects of Reynolds number were found for flow in the supersonic Mach number to a maximum of approximately 2.1 at a Mach number of unity. In the supersonic Mach number range, the drag coefficient decreased with increasing Mach number to a value of about 1.34 at a Mach number of 2.9. Drag data from other investigations have been included for comparison.
language	English
title	NACA-TN-2960	num
title	Drag of circular cylinders for a wide range of Reynolds numbers and Mach numbers	en
type	standard
page	27
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1953
contenttype	fulltext