Abstract
Numerical investigation of flow around an hemispherical nose cone missile was simulated for very low speed flow conditions. The geometry creation, meshing of geometry, solving and post processing was done in ANSYS - Fluent. This research uses CFD at the subsonic range to analyze missiles with hemispherical nose cones at various angles of attacks from 0° to 16° with step of 4° deg and different velocity ranging from 5 m/s to 20 m/s. This study estimates the aerodynamics characteristics such as the coefficient of drag and lift. Besides, distribution of the coefficient of pressure over the surface of the hemispherical missile nose cones and their graphical result are ploted and presented.
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