The conventional steps of defining performance requirements of an aircraft wing and conducting general sizing of the wing are followed by the new steps of determining the aerodynamic sweep angle of the wing with respect to an actual location of a shock wave on the wing. A two dimensional Mach number for the wing airfoil is calculated by multiplying the three dimensional Mach number by the cosine of the aerodynamic sweep angle. A two dimensional lift coefficient for the wing airfoil is calculated by dividing the three dimensional lift coefficient by the square of the cosine of the aerodynamic sweep angle. Airfoil shape in two dimensions is determined on the basis of the two dimensions is determined on the basis of the two dimensional Mach number and the two dimensional lift coefficient. The shape of the wing in three dimensions is then defined by placing the airfoil in the wing along an arc constructed by skewed chord lines perpendicular to local sweep lines of the wing at a series of locations along a chord of the wing.
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