ESDU 81014:2013

$89.05

Contribution of wing planform to derivatives of yawing moment and side force due to roll rate at subsonic speeds, (Np)w and (Yp)w

Published By	Publication Date	Number of Pages
ESDU	2013-08-01	36

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Description

ESDU 81014 presents a method of estimating the planform
contribution to the yawing moment due to roll-rate, (Np)w, and the
sideforce due to roll rate, (Yp)w, of swept wings at subsonic
speeds. The method applies to wings without dihedral, camber or
twist, in the "clean condition", i.e. with any high-lift devices
retracted. The method was originally developed for untapered wings
but data have been provided to take into account the small effect
of wing taper. The method for the sideforce derivative applies only
over the range of lift coefficients for which the flow is attached
to the wing surface and (Yp)w varies linearly with lift
coefficient. In the case of the yawing moment derivative, however,
the data provide an empirical means of extending the estimation
into the range of lift coefficients in which areas of flow
separation exist and (Np)w varies non-linearly with lift
coefficient and often changes sign at a moderate to high lift
coefficient. The knowledge provided by the data of where such a
change in sign occurs is very important to the designer in
assessing the stability of an aircraft. The data cover an aspect
ratio range from 2 to 12, wing sweepback angles up to 60 degrees
and Atan? ¼ = 6. The first-order effects of subsonic Mach number
are also catered for. A computer program of the method is provided
as ESDUpac A8114.