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This paper presents the computer implementation process of the Panel Method for aerodynamic analysis of three dimensional bodies with or without lift. The computer implementation consists in the creation of pre and post processing environments and a solver for the solution of the problem in external flow potential over three dimensional bodies with and without lift. For cases in which there’s no lift, a constant distribution of sources over the body (fusaleges, farings, etc.) is used, their intensities calculated in order to guarantee impermeability of the body. For cases in which there is lift, a constant distribution of sources and doublets are used on the body (wings, tails, etc.). The intensity of the sources is solved in the same manner as cases with no lift. Intensity of doublets is solved in order to satisfy the equality condition regarding pressure on the under and upper side of the trailing edge (Kutta Condition) of the body without lift.

This paper describes the design of an International Formula One (IF1) racing airplane wing. The first step consists in the simulation of the airplane flying on the race track to obtain details about the condition in which the wing needs to be designed and optimized. The paper describes the details and formulation used to perform this simulation using parametric flight paths and a point model dynamic model. A scheme analytically obtains the control laws for the simulation with Frenet-Serret frames over the parametric flight path. Two different airplanes, with different power levels, are simulated on a typical IF1 race track to determine the range of lift coefficient in which the wing must be designed. Based on this lift coefficient range, a set of four new airfoils are designed based on the NLF0414-F airfoil. Their usage over the wing span is determined, using nonlinear lifting line method to assure that during races the wing operates inside the laminar drag bucket.