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The flow field in the supersonic mixed compression axisymmetric as well as two-dimensional intake have been investigated numerically. The flow characteristics, such as pressure, temperature, and velocity have been obtained. An enlarged chamber with a supersonic convergent-divergent nozzle has been integrated at the air intake exit to simulate the ramjet engine. Suitable heat addition at the inner surface of the wall has enabled the simulation of combustion chamber condition. The well-known modes of operation of the ramjet engine air intake have been predicted by the mathematical simulations. A comparative study for supercritical, critical, and subcritical -;conditions has been presented. The predicted flow features including shock locations and the static pressure distributions along the cowl, as well as the centre body are in agreement with the available experimental results in the published literature. The effect of thermal input in the combustion chamber on the flow characteristics of the air intake has been studied in detail. The characteristic curve of generic supersonic air intake can be obtained through these numerical studies.

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