NACA-RM-L56H06

Longitudinal and lateral stability characteristics of a low-aspect-ratio unswept-wing airplane model at Mach numbers of 1.82 and 2.01

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T16:35:46Z
date available	2017-09-04T16:35:46Z
date copyright	01/01/1956
date issued	1956
identifier other	VAYIYDAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/99239
description abstract	INTRODUCTION An investigation has been made in the Langley 4- by 4-foot supersonic pressure tunnel at Mach numbers of 1.82 and 2.01 to determine the static longitudinal and lateral stability characteristics of a model of a fighter-type airplane having low-aspect-ratio unswept wings. The complete model and various combinations of its components, including a modified vertical tail and several ventral-fin arrangements, were tested through an angle-of-attack and sideslip range. In addition, the effects of a pylon-mounted fuselage store, two wing-tip-mounted missile configurations, and wing-tip fuel tanks were determined. The tests were made at Reynolds numbers of 1.38 x 10⁶ and 1.02 x 10⁶ (based on the wing mean geometric chord) for Mach numbers of 1.82 and 2.01, respectively.
language	English
title	NACA-RM-L56H06	num
title	Longitudinal and lateral stability characteristics of a low-aspect-ratio unswept-wing airplane model at Mach numbers of 1.82 and 2.01	en
type	standard
page	71
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1956
contenttype	fulltext