The problem is considered of a wing with rectilinear plan form swept SO that both, leading and trailing edges lie within their respective Mach cones; moreover, the Mach lines from the trailing-edge apex intersect the leading edge. Formulas and design charts are presented for the lift in such a case, based on approximate formulas for the lift distribution developed in NACA TN 1991, 1949. The charts cover a practical range of aspect ratios and plan forms of moderate taper, with tips parallel to the stream. The leading-edge thrust and drag due to lift are also readily calculated from the material presented. Numerical results and an applica-tion of the charts are included.
展开▼
