A Conceptual Design Methodology for the Estimation of the Local Shock Locations on Optimized Transonic Wings

Summary

A conceptual design methodology shall be developed for use within multidisciplinary aircraft design. The methodology estimates the local shock locations on the upper surface of wings being optimized with respect to total drag as a function of the design parameters Ma, t/c, c _L and Re. In order to achieve this a database of drag optimized cross sections, called optimized performance designs, was analyzed accordingly. A methodology to estimate the local shock sweep angle using the method for the local shock locations as a function of the design parameters and the wing planform was derived. The methodology to estimate the local shock sweep angle will be used within another conceptual design method to predict the minimum wave drag of a transonic wing.