Abstract
A exploratory investigation into the construction of semiempirical, analytic expressions for steady, symmetric flow characteristics on thin rectangular wings at transonic speed is presented. Early contributions from the small-disturbance transonic flow theory are used as a guide. These solutions for two-dimensional wings with rombic sections, extending over most of the supersonic portion of the transonic region, are represented by analytic expressions obtained through modification of corresponding expressions prepared for subsonic flow. The result is applied on a wing with an aspect ratio of 2 and three thickness-to-chord ratios. Experiments for comparison are not available.
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