An automated design optimization process is applied to both single and multi objective optimization problems of scramjet inlet design. This optimization process integrates together an optimizer with a mesh generator, a flow solver, and an objective analysis tool into an automated optimization loops because the flow simulation is required for every step along the line search and finding the feasible direction. This paper presents the implementation of these new design techniques by the gradient-based optimizer Sequential Quadratic Programming (SQP) and their application to scramjet inlet case in flight condition of Mach 8. The performance of scramjet inlets with uniform inflow is improved, and the optimized functions, that is, the total pressure recovery co-efficient increases by approximately 10%. The trade-off (also known as the ε-constraint) method is applied and implemented to find the Pareto optimal set formed by the non-dominated solutions of the feasible design. The objective functions are the total pressure loss and the drag, and some solutions are obtained to analyze the relations between the total pressure loss and the drag.