Numerical Analysis of Nose shape on the Aerodynamic Characteristics of Rocket

Muna S. Kassim†, Firas A. Abbas‡, Israa Ali Abdulghafar‡†, Laith Jaafer Habeeb‡‡

†College of Engineering, Mustansiriyah University, Iraq-Baghdad

‡Gas filling company, Ministry of oil, Iraq-Wassit

‡†Middle Technical University, Iraq-Baghdad

‡‡Training and Workshops Center, University of Technology, Iraq-Baghdad

Corresponding Author Email: munakassim@uomustansiriyah.edu.iq, laithfiras3@gmail.com,Israaali485@yahoo.com 

This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

Air flowing round model rockets by means of different nose geometries has been investigated during this study. The mathematical related computational fluid dynamics techniques applied for the investigation is presented and a computational model is developed using ANSYS FLUENT R 19.2 software. Pressure contours, airflow path lines, and drag coefficient depending on the rockets velocity are presented. The most suitable nose shape for the rocket is selected. Results of numerical simulation showed that the maximum drag coefficient was with spline nose in all velocities. It has been found that at all velocity ranges, the lowest drag coefficient is with elliptical nose.