A computational fluid dynamics code was developed to compute the flow inside and around a supersonic external compression axisymmetric intake. The code solves the Reynolds-averaged Navier–Stokes equations using an explicit finite volume method in a structured grid and uses the Baldwin–Lomax algebraic model to compute the turbulent viscosity coefficient. Experiments were performed to validate the predicted results and good agreements are achieved. In the next part of the research, a parametric study was undertaken using the designed base case at a constant Mach number of 2 and at 0° angle of attack. The effects of various important parameters such as free stream Mach number, spike deflection angle, and back pressure ratio on the total pressure recovery, mass flow ratio, flow distortion, and drag coefficient of the intake were then numerically investigated. The results showed that when the spike deflection angle of the intake was changed from 28° (designed base case) to 30°, the intake drag coefficient was reduced up to 9%. In addition, the intake performance degraded for very low values of the back pressure ratio.

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