Keywords:Aerodynamics, Structures, Design
AbstractA simple method is given for determining trim drag coefficient, trim drag being the increase in induced drag by the wing-tailplane combination above the norninal value calculated from the usual approximation in which the effect of the tail load is ignored. The method has been used to derive trim drag coefficients for low- and T-tail locations for a range of parameters including C. G. position. For the T-tail it is necessary to know the location of the wing vortex sheet at the tailplane position and a simple rule of thumb for determining this is derived. Comments on optimum wing-section camber and C. G. position are made.
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