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Planar inlet concepts play an important role in the design of supersonic propulsion systems. The inlet reduces the speed of supersonic flow by the oblique shock wave or an array of oblique shock waves and a final normal shock provides the subsonic flow after the throat of the diffuser. In this paper, a design method of Mach 3.0 supersonic multi-ramp inlet is explained, the geometry is designed and simulated by the numerical solver. Designing the inlets for the high supersonic Mach range, between 3 and 5 is very challenging because of the viscosity interactions and the related effects on the propulsive efficiency. The considered inlet in this study is a mixed system which provides the required compression by the combination of the three external ramps and a subsonic diffuser. A computational code calculated the optimum dimensions numerically and a second order CFD solver has simulated the inlet operations by the accuracy of 10E-05. In addition to aerodynamic performance, Advantages and problems of such a combination, development of boundary layer and its interactions with the normal shock and performance of bleeding mechanism are simulated and studied. Finally, this paper presents compact details of design, simulation and viscosity effect of mixed compression surface.

Keywords: Supersonic mix compression system, multiramp inlet, Airbreathing propulsion, numerical simulation, boundary layer effects

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