Scramjet propulsion provides promising opportunities for high speed transportation and cost reduction for satellite and spacecraft launch operations. Recent successes in flight demonstrations of Mach 7 to 10 flight speeds of the HyShot and Hyper-X programs have in part attributed to computational capabilities of the research teams in complimenting the understanding of the complex flow physics in this stringent and demanding flight regime. This paper provides some selected numerical examples among the abundance of available test cases for the purpose of demonstrating to what extends the current computational models can do in assisting the design and test programs in scramjet research. Numerical examples of different scramjet combustor designs are investigated with benchmark data validations. Ideas of future developments and applications of the present numerical model are also outlined and discussed.