The purpose of this study is to modify and optimize the configuration of the Airborne Missile Launcher Pod (AMLP) to extend its usage from ground or helicopter mounting to the fixed-wing aircraft where the aerodynamic drag becomes important. Many engineering problems need a multi-objective optimization approach to generate an optimal strategy for decision making. The objectives considered in this study are the aerodynamic drag coefficient, the mass, and the cost of the AMLP. The methodology used to find the optimum strategy was the Multi-Objective Decision Analysis (MODA) process which is combined with statistical techniques to generate mathematical regression models of configuration variables. These models were used in the optimization of the system. The drag coefficients were obtained from Computational Fluid Dynamics (CFD) simulation where Central Composite Design (CCD) method was used to decrease the expensive CFD computation. The model for mass (or volume) was generated from the linear regression analysis. Then, the weighting Min-Max method in combination with the constrained method was used to determine the optimal values for the modified AMLP. Weighting combination of objectives was generated to demonstrate the Pareto set for the best solutions. The configuration obtained from this study can be provided to stakeholders for objective evaluations and help to make the decision to choose the best solution.