Prediction of Aerodynamic Characteristics for Slender Bluff Bodies with Different Nose Cone Shapes

Abstract

In this work, the numerical approach is used to verify the aero/hydrodynamic performance of different geometries of nose cones. Computational methods predict the flow characteristics fairly accurately in order to validate the data obtained from experiments. The simulation involves muzzle velocity that range from 5 m/s to 25 m/s the corresponding Reynolds numbers ranges from 1.69 to 8.4 x 105 and calculated for the different angle of attack, -10 to 20 degrees, to demonstrate the flow behavior around the different nosecone shaped shells. Nosecone is the most forward section of any slender moving bodies which are used in rockets, guided missiles, submarines, aircraft drop tanks and aircraft fuselage to reduce the aerodynamic or hydrodynamic drag. The basic geometry of bluff body is cylinder with variant nosecone shapes such as flat and tapered head, with moderate to low taper ratios and conical head. The aerodynamic characteristics like lift, drag and pressure distribution of the cylinder with different nosecones are illustrated for low subsonic speed for the same length to diameter ratio. The best results are obtained for cylinder with conical nosecone and better similar results observed for cylinder with shapes having low and medium taper.