Numerical Research Of Flow FieldofFins Rocket

The rocket has many advantages, such as great power, density of fire intensity, flexibilityand has favorable firepower rapid attack, etc. Currently, it has become a very powerfulconventional weapon. Aerodynamics has great impact on the rocket range, stability anddistribution characteristics. It can obtain a lot of useful aerodynamic parameters (such as dragcoefficient and lift coefficient) through the research on circle flow field of the rocket. Flowvariation can be obtained by numerical simulation, then the main factors of rockets tacticaland technical will be determined. Compared with the theoretical analysis and experimentalstudy, numerical simulation on the flow field can not only save a lot of manpower, materialresources, but also can significantly shorten the design cycle. So, the research on circle flowfield of the rocket has great significance. This paper uses the FLUENT software to simulatethe circle flow field of the common shell and the rocket of three kinds of head shape undereach work conditions. Contrasting with the common shell will be a good way to studyinfluences on aerodynamics which owes to the changes of the rocket shape.Firstly, the mathematical and physics models of 3D circle flow field were set up in thepaper, basing on the characteristics of the rocket; It can get clear pressure contours, Machcontours, density contours, velocity vector at the tail by the simulation of three kinds of headshape of rocket; It analyzed the characteristics of the flow structure on the shape of rocketwarheads. Secondly,using the FLUENT software to simulate the head of the conical rocketmodel at 0 degrees angle of attack, the results obtained is consistent with the experimentalresults and verify the model and software used in the correct. Finally, at 5 degrees of angle ofattack, the three different head shapes rocket on aerodynamics coefficients variation withMach number is studied such as drag coefficient, lift coefficient and pressure centercoefficient. It provides rocket engineering design for the technical support.