Aerodynamic analysis of (GRAD (Rocket using (CFD)

Abstract

In this research, The aerodynamic coefficients and stability derivatives for supersonic )GRAD( rocket in active and passive phases have been calculated. The modifications have been implemented are ogive nose shape and increased in fins number. The impacts of fins configuration and setting angle have been also demonstrated. The Computational Fluid Dynamics and Missile Datcom are used in the simulation. The study has adopted three different configurations of WAFs for rocket and single domain technology to investigate the lateral and rolling characteristics of WAFs, including the fins setting angles. Simulation has been performed at Mach numbers ranging from 0.4 to 3 through angle-of-attack and side slip angle from zero to 9 degree. The result represents that the wrapped around fins (WAF) configuration is greatly improved the longitudinal stability and enhanced the longitudinal aerodynamic characteristics for the rocket. The total drag of the rocket is mainly stemmed from the body, while the drag generated by the WAF account for only about 18.45 per cent. Maintaining negative fins setting angle is provided additional side and rolling moments which enhanced lateral and longitudinal stability. Both, lateral and longitudinal stability are investigated. Simulation captured Shock wave at missile’s nose and fins, and represented the flow properties around missile configuration. The Missile Datcom software was used to verify and validate the CFD’s results and the results comparison showed satisfactory agreement between the two different solutions.