A Study on the Reduction of Drag and Heat Transfer on a Conventional Hypersonic Nose Cone

In the present study, the effect of jet injection on two geometries—single-cone and double-cone—subjected to hypersonic flow is investigated. The simulations are performed using ANSYS-Fluent software. The baseline case is one where the nose lacks injection. The single-cone nose is tested at Mach ۶, and the double-cone nose at Mach ۵.۴. The results show that increasing injection pressure results in a drag coefficient reduction of ۴۹.۲% for the single-cone geometry and ۶۲.۷% for the double-cone geometry, compared to the baseline. Additionally, the heat flux decreases by ۶۰% for the single-cone nose and ۴۱.۳% for the double-cone nose. Higher injection pressure leads to an increase in bow shock standoff distance upstream of both the single-cone and double-cone noses. Increasing injection temperature has minimal impact on the drag coefficient and pressure distribution on the surface of the single-cone nose but significantly reduces the Stanton number, thereby decreasing heat transfer and enhancing nose cooling. Increasing the injection diameter from zero to ۵ mm in the single-cone nose results in a ۲۳% reduction in drag coefficient, while for the double-cone geometry, increasing the diameter to ۱۶.۵ mm reduces the drag coefficient by ۷۵.۰۴%. Changing the fluid type from air to a gas mixture decreases the maximum Stanton number by ۱۹.۳%.

کلیدواژه ها:

Single-Cone Nose ، Double-Cone Nose ، Stanton Number ، pressure distribution ، Drag Coefficient