Aerodynamic analysis in the conceptual aircraft design process requires drag prediction for a wide range of aircraft configurations under various operating conditions, considering different combinations of lift coefficient, Mach number, and Reynolds number. These drag predictions must be achieved within a fast turnaround time to support aircraft conceptual design, meaning the ability to exploit high fidelity CFD methods is highly limited. Hence, traditionally designers have relied on empirical-based regression equations for drag prediction, due to their rapid execution and minimal reliance on detailed external geometry. Indeed use of empirical-based drag prediction for skin friction, form drag, and induced drag has proven highly valuable for conceptual design associated with many different aircraft requirements. However, for an aircraft operating at transonic conditions, compressibility effects and the development of shock waves means wave drag, together with its variation with operating conditions, must also be predicted. In addition, non-linear drag divergence and the potential for shock induced boundary layer separation, will each limit the range of viable operating conditions associated with a transonic aircraft design and must be accurately addressed in the conceptual design stage. To address the limitations of traditional methods for including shock wave effects in conceptual design, this work presents a rapid aerodynamic analysis method for transonic drag assessment for a wide range of wing-body configurations. The methodology employs the Viscous Full-Potential (VFP) method to conduct aerodynamic ¬analysis for wing-body configurations, involving the determination of both global and local aerodynamic coefficients [1]. The VFP method utilizes a semi-inverse viscous-coupled scheme for predicting the boundary layer properties and incorporates a field-based wave drag post-processing module to identify shock waves and their properties [2]. This study involves the rapid computation of off-design aerodynamic performance maps for a range of transonic wing planform designs. Particular attention will be given to investigating the trade-off between drag divergence boundary, onset of separation, combined with viscous and wave drag characteristics, by varying wing planform parameters. Furthermore, the accuracy and efficiency of the proposed method will be compared with existing empirical-based methods.