NACA-TR-971

NASA - National Aeronautics and Space Administration (NASA)

Theoretical stability derivatives of thin sweptback wings tapered to a point with sweptback or sweptforward trailing edges for a limited range of supersonic speeds

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NASA - National Aeronautics and Space Administration (NASA)

Year: 1950

Abstract: The stability derivatives valid for a limited range of supersonic speeds are presented for a series of sweptback wings tapered to a point with sweptback or sweptforward trailing edges. These wings were derived by modifying the trailing edge of a basic triangular wing so that it coincided with lines drawn from the wing tips to the wing axis of symmetry. The stability derivatives were formulated by using the pressure distributions previously obtained for the basic triangular wing for angle of attack, constant vertical acceleration, sideslip, pitching, rolling, and yawing. Explicit expressions are given for the stability derivatives with respect to principal body axes, and conversion formulas are provided for the transformation to stability axes. The results are limited to Mach numbers for which the wing is contained within the Mach cones springing from the vertex and from the trailing edge of the center selection of the wing.

URI: http://yse.yabesh.ir/std;jsessionid=3826AF679D40527318548F1EFDEC014A/handle/yse/226075

Subject: AERODYNAMIC

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NASA - National Aeronautics and Space Administration (NASA)

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contributor author	NASA - National Aeronautics and Space Administration (NASA)
date accessioned	2017-09-04T18:44:35Z
date available	2017-09-04T18:44:35Z
date copyright	01/01/1950
date issued	1950
identifier other	KFDZYDAAAAAAAAAA.pdf
identifier uri	http://yse.yabesh.ir/std;jsessionid=3826AF679D40527318548F1EFDEC014A/handle/yse/226075
description abstract	The stability derivatives valid for a limited range of supersonic speeds are presented for a series of sweptback wings tapered to a point with sweptback or sweptforward trailing edges. These wings were derived by modifying the trailing edge of a basic triangular wing so that it coincided with lines drawn from the wing tips to the wing axis of symmetry. The stability derivatives were formulated by using the pressure distributions previously obtained for the basic triangular wing for angle of attack, constant vertical acceleration, sideslip, pitching, rolling, and yawing. Explicit expressions are given for the stability derivatives with respect to principal body axes, and conversion formulas are provided for the transformation to stability axes. The results are limited to Mach numbers for which the wing is contained within the Mach cones springing from the vertex and from the trailing edge of the center selection of the wing.
language	English
title	NACA-TR-971	num
title	Theoretical stability derivatives of thin sweptback wings tapered to a point with sweptback or sweptforward trailing edges for a limited range of supersonic speeds	en
type	standard
page	14
status	Active
tree	NASA - National Aeronautics and Space Administration (NASA):;1950
contenttype	fulltext
subject keywords	AERODYNAMIC
subject keywords	AIRCRAFT
subject keywords	COMPUTATIONAL
subject keywords	DELTA
subject keywords	DISTRIBUTION
subject keywords	DYNAMICS
subject keywords	EDGES
subject keywords	EFFECT
subject keywords	FLOW
subject keywords	FLUID
subject keywords	LOADING
subject keywords	PARTS
subject keywords	PRESSURE
subject keywords	STABILITY
subject keywords	SUPERSONIC
subject keywords	SWEEP
subject keywords	SWEPT
subject keywords	THIN
subject keywords	TRAILING
subject keywords	WING
subject keywords	WINGS