NACA-RM-A7K28

High-speed stability and control characteristics of a fighter airplane model with a swept-back wing and tail

contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T15:44:04Z
date available	2017-09-04T15:44:04Z
date copyright	01/01/1948
date issued	1948
identifier other	POCTUDAAAAAAAAAA.pdf
identifier uri	https://yse.yabesh.ir/std/handle/yse/46436
description abstract	INTRODUCTION This report present the high-speed stability and control characteristics of a fighter airplane model with a 35° swept-back wing and tail. The data presented herein were obtained form tests made in the Ames 16-foot high-speed wind tunnel of a semispan model of the airplane. For results of other tests conducted with the same model, consult references 1 and 2 which cover modifications to the original model and the effects of external stores, respectively. The high-speed data contained in this report included the basic aerodynamic characteristics of the model, the effectiveness and hinge-moment characteristics of the control surfaces, the effect of wing leading-edge slats, and the effect of the fuselage-sode dive crakes.
language	English
title	NACA-RM-A7K28	num
title	High-speed stability and control characteristics of a fighter airplane model with a swept-back wing and tail	en
type	standard
page	49
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1948
contenttype	fulltext