The innovative BEM solver has been successfully proven a feasible 3-D tool for CSD/CFD interfacing, as supported by the results of the five aeroelastic test cases performed in Phase I. The specific technical objective of Phase II is to further enhance the geometric generality, solution accuracy, computational efficiency of the 3-D BEM solver and lastly to develop a versatile and user-friendly production code with an integrated GUI system. This above objective will be achieved by (1) developing a high-order BEM solver to drastically reduce the size of the problem, (2) incorporating the multi-block capability for discontinuing structures, (3) developing interface modules between CFD/BEM and BEM/NASTRAN to minimize required user input to problem set-up, (4) implementing the parallel computing capability to fully explore the parallelization of the BEM solver, and (5) integrating a GUI system for the pre/postprocessor of the BEM solver. The developed 3-D BEM solver will be validated by the selected aeroelastic test cases that include (1) steady and transient response of the AGARD 445.6 wing, (2) F-16 wing-body configurations, (3) wing and twin tail delta wing configuration and (4) full F-15 aircraft. The 3-D BEM solver, once developed, will be a successful end product for NASA and commercialization applications.