| In the supersonic flight, a huge amount of friction is produced and causes heat on the aircraft’s body. That heat on the aircraft’s body can be reduced by generating a strong shock wave. The strong shock wave can increase the temperature of the air flow around aircraft’s nose, so the heat causes by air friction could be carried away by the high temperature air flow around aircraft’s nose. Therefore, the heat on the aircraft’s body can be reduced. Nose cones t hat have a blunt shape produce stronger shock wave than those with a sharp shape, however they produce a higher drag. The objective of this study is t o determine t he geometry of aircraft’s nose that can produce a strong shock wave in supersonic flight while maintaining a low drag. Numerical simulations are done using ANSYS FLUENT to analyze the phenomena around various nose’s shapes and radius in a flow of 3,048 Mach. The shapes of the aircraft’s nose tested are conical, ¾- parabolic, ¾- power, and Von Karman. The variations of radius tested for each shape are 5, 10, 15, 20, 25, and 30 mm with the nose length of 50 mm. Based on that simulations, the aircraft's nose with ¾-parabolic shape and a fineness ratio of 10 (radius 5 mm) is the best geometry for supersonic aircraft. This happened because the aircraft’s nose with ¾--parabolic shape with a fineness ratio 10 (radius 5 mm) have the lowest drag and the best thermal design compared to other shapes. |