An airfoil design method is proposed which considers the boundary-layer integral parameters as the driving design condition. The method consists of a parameterization for generation of a pressure distribution capable of producing desired boundary-layer characteristics, which is then used to obtain a corresponding airfoil geometry through an inverse design approach. More specifically, the pressure distribution that results in the minimum θT E condition is considered since, by deduction from the Squire-Young theory, it would produce the minimum drag. As a case study, the LRN1015 airfoil was considered as a seed geometry and modified based on the mission requirements of the RQ-4B Global Hawk. Numerical results obtained using a viscous-inviscid Euler simulation showed that the optimized airfoils achieved Cd reductions of 9.06% and 6.00%, respectively, for the α = 0◦ and L/Dmax design points considered.