Comparative Study on Nose Cones with respect to Angle of Attack using CFD

Abstract

A nose cone is the conically shaped forward most section of a rocket, guided missile or aircraft, designed to modulate oncoming airflow behaviours and minimize drag. In this paper, the authors analysed by means of a computational procedure the influence of varying the angle of attack for shapes of rocket nose cones in each of them, with this analysed and calculated the values of the, coefficient of lift and the coefficient of drag generated by our nose cones having as a working parameter in subsonic medium ranging from a Mach 0.03 to approximately 0.50, considering standard conditions for temperature and pressure. Drag and Lift both are aerodynamic forces which need to be calculated for cones. Objects with every kind of shapes experience a significant magnitude of Cl and Cd from airflow with the use of the ANSYS platform based on the CFD Fluent method it was possible to measure behaviour in the 3 shapes of cones and thus analyse the different contours. We showed the variation of pressure and velocity with their graphs. The scope of this paper is to simulate the different nose cones with different angle of attack for taking out the best result and comparing which one cone is best for which angle of attack.