ESDU 72021:2009

$62.40

Effect of wing on rolling moment due to yawing

Published By	Publication Date	Number of Pages
ESDU	2009-11-01	21

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INTRODUCTION

The data given in this Item provide a means of estimating the
contribution of a straight-tapered swept wing to the rolling moment
derivative due to yawing at lift coefficients for which the flow
remains fully attached (see Item No. 66033 for wings with
symmetrical sections) and at Mach numbers for which the flow is
subsonic over the whole of the wing. Some data are included for
slender wings of delta and gothic planform.

The basic planform contribution (p) and the
contributions due to dihedral (G), twist (e) and deflected trailing
edge flaps (f) can be taken into account,
i.e.