Numerical Investigation on Shock-Wave and Boundary-Layer Interactions Inside the Axisymmetric and Planar Scramjet Intakes with Different Cowl Orientations

The computational investigations of planar and axisymmetric scramjet intakes with different cowl configurations have been carried out to study the shock-wave/boundary-layer interaction (SWBLI) at Mach 4.03. The 2D numerical simulation has been conducted using the finite volume solver Ansys Fluent. The velocity contour for both the planar and the axisymmetric intakes with straight and bent cowls is analyzed to find the superior intake geometry which can be efficient in suppressing the separation bubble, formed due to SWBLI. It is observed that the axisymmetric intake is very effective in suppressing the separation bubbles. Interestingly, for both the planar and the axisymmetric intakes, the separation bubble is washed away from the bent cowl. Besides, the wall static pressure distribution for both planar and axisymmetric intakes with straight and bent cowl reveals that wall static pressure is less for axisymmetric intake when compared to planar intake. For both the axisymmetric and planar intakes, the shock strength is lesser for the bent cowl, which is evident from the wall pressure plot. In addition, the study has been extended specifically to make a direct comparison between the planar and the axisymmetric intakes. The total pressure at the isolator exit is higher for axisymmetric intake which conveys that the axisymmetric intake is very effective in conserving the total pressure of the incoming flow. The temperature plot over the ramp surface shows that the temperature is higher for planar intake; however, the temperature fluctuations over the ramp surface are more for axisymmetric intake.