Abstract
UTILIZING THE techniques outlined in references 1 and 2, it is a fairly simple matter to determine the aerodynamic lift, pitching moment, side force, and yawing moments due to angle of attack, pitching angular velocity, sideslip, yawing angular velocity, and the rates of change of these quantities for the slender configuration shown in Fig. 1. I t is more tedious but none the less straightforward to find the above-mentioned forces and moments due to rolling angular velocity and its rate of change as well as the rolling moment due to all the previously mentioned motions. The only requirement is that one find the conformal mapping of the cross section of the configuration (see Fig. 2) onto a circle with no distortion at infinity. If we call the crosssection plane the z plane and the circle plane the f plane, this conformal mapping is given by:
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