Abstract:

Presents data for the contribution of a straight-tapered swept wing to the aero-normalised yawing moment derivative due to yawing in low-speed flow at lift coefficients for which the flow remains fully attached. The method expresses the yawing moment in terms of two components. One is proportional to the wing zero-lift drag coefficient, being associated with the asymmetric distribution of profile drag. The other is proportional to the square of the wing lift coefficient, being associated with the asymmetric distribution of the lift-dependent drag due to the trailing vortex system. An approximate method allowing for the deployment of trailing-edge flaps is included, in terms of the flap induced increment to the zero-lift drag coefficient.