NACA-RM-L52K24

Wind-tunnel investigation to determine the aerodynamic characteristics in steady roll of a model at high subsonic speeds

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T18:16:45Z
date available	2017-09-04T18:16:45Z
date copyright	01/01/1952
date issued	1952
identifier other	HNSWXDAAAAAAAAAA.pdf
identifier uri	http://yse.yabesh.ir/std;jsery=autho162s7D8308/handle/yse/199697
description abstract	INTRODUCTION A general research program is being carried out the Langley high-speed 7- by 10-foot tunnel to determine the aerodynamic characteristics in pitch, sideslip, and steady-roll of various model configurations. This paper presents data obtained during steady-roll tests of a complete swept-wing model and its component parts. The wing and horizontal tail of the model were swept back 45º at the quarter-chord lines and the vertical tail was swept back 55^º at the quarter-chord line. The sting-mounted model was tested through a Mach number range 0.40 to approximately 0.95 which gave a mean test Reynolds number range based on the mean aerodynamic chord of the wing from about 1.8 x 10 ⁶ to approximately 3.0 x 10⁶. Static longitudinal stability characteristics the wing-fuselage combination of the present model are presented in reference 1.
language	English
title	NACA-RM-L52K24	num
title	Wind-tunnel investigation to determine the aerodynamic characteristics in steady roll of a model at high subsonic speeds	en
type	standard
page	40
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1952
contenttype	fulltext