A hybrid computational fluid dynamics procedure for sonic boom predi ction is presented. The method begins with either Euler or Navier -Stokes unstructured mesh computations with mesh refinement adaptation performed to efficiently resolve the solution to a high degree of resolution in the extreme -near -field of the aircraft. Flow fi el d data is extracted from the unstructured mesh solution along a cylinder existing within the adapted region. This data is used as boundary conditions for an Euler structured mesh computation to resolve the pressure field several body lengths away from the aircraft. The method leverages advantages of both unstructured and structured meshes while avoiding many of their disadvantages. Near -field pressure measurements predicted using the method are compared to wind tunnel measured pressure data of two NASA shape sonic boom aircraft models. Comparisons to Shaped Sonic Boom Demonstrator flight test data are also presented. Results indicate that the method can confidently be used for sonic boom predictions.