NACA-RM-L52J17

An investigation at Mach numbers of 1.41 and 2.01 of the aerodynamic characteristics of a swept-wing supersonic bomber configuration

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T16:40:02Z
date available	2017-09-04T16:40:02Z
date copyright	01/01/1956
date issued	1956
identifier other	VMSWXDAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/103749
description abstract	INTRODUCTION An investigation of a swept-wing supersonic bomber configuration has been made in the Langley 8-foot transonic tunnel (ref. 1) and the Langley 4- by 4-foot supersonic pressure tunnel This report presents the results of the investigation in the latter tunnel at Mach numbers of 1.41 and 2.01, and a Reynolds number of 2.5 x 10⁶ based on wing mean aerodynamic chord. Longitudinal and lateral force characteristics of the complete aircraft configuration and of various combinations of its components, including several jet nacelle installations, are shown. The effects of a modified wing, a shortened fuselage and two horizontal-tail heights were also studied. Some comparisons of the data with simple theories are presented.
language	English
title	NACA-RM-L52J17	num
title	An investigation at Mach numbers of 1.41 and 2.01 of the aerodynamic characteristics of a swept-wing supersonic bomber configuration	en
type	standard
page	92
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1956
contenttype	fulltext