Author/Authors :
Kassim, Muna S. Mustansiriyah University, Baghdad, Iraq , Abbas, Firas A. Ministry of oil - Gas filling company, Wassit, Iraq , Abdulghafar, Israa Ali Middle Technical University, Baghdad, Iraq , Habeeb, Laith Jaafer Training and Workshops Center - University of Technology, Baghdad, Iraq
Abstract :
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.
Keywords :
3D Simulation , Airflow , Drag coefficient , Nose shape , Pressure distribution , velocity distribution
