Conventional steps of defining the performance requirements of an aircraft wing and determination of the general dimensions of the wing are followed by the further steps of determining the aerodynamic sweep angle of the wing relative to an effective point of a shock wave on the wing. A Mach number of two-dimensional to the airfoil is calculated by multiplying the number of Mach-dimensional by the cosine of the aerodynamic sweep angle. A two-dimensional lift coefficient for the airfoil is calculated by dividing the three-dimensional lift coefficient by the square of the cosine of the aerodynamic sweep angle. The shape of the aerodynamic profile in two dimensions is determined based on the number of Mach-dimensional and two-dimensional lift coefficient. The wing shape in three dimensions is then defined by placing the airfoil in the wing along an arc constructed by oblique rope lines perpendicular to the local arrow lines of the wing at a series locations along a wing chord.
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