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This paper presents a study of the effects of total pressure and temperature conditions at the inlet of a dual-stream nozzle. The design and operating conditions of the nozzle are typically those of an aircraft engine. Major part of the study has been performed with RANS computations on an axisymetrical mesh. Variations of inlet conditions consist in a variation of values injected and in the use of profiles as boundary conditions. The article focuses on the effects on the mass flow, the shock-cells positioning and the closeto exit region velocities. Results are compared with experimental data. The effect of inflow boundary conditions is quantified and the interest of non-uniform profile injection in the fan channel is exhibited. Some computations enforcing ZDES (Zonal Detached Eddy Simulation) are performed and enable to analyze turbulent variables into more details.