A complete dual mode scramjet assembly code was built using Numerical Propulsion Simulation System and the performance of the engine was tested for an envelope of Mach number 3.5 to 6.0. Different numerical techniques were opted for varying the fidelity of the analysis with the highest fidelity consisting of 2D RANS CFD simulation. The interaction between the NPSS elements with the CFD solver was governed by the top level assembly solver of NPSS. The results of intercomponent interaction between the compression components with the rest of the engine after varying the fidelity of the numerical simulation according to the complexity of the situation are presented. The length of the shock train has been predicted using different methods. The transition Mach number where operation switches from ramjet to scramjet mode was also studied. The results stress the importance of accounting for intercomponent interactions during the design phase of the components.

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