Numerical simulation of lateral jets in supersonic crossflow of missiles using computational fluid dynamics

Dağlı, Efe Can
In this thesis, numerical simulation method for modelling lateral jet in supersonic crossflow is presented. Lateral jet control provides high maneuverability to the missile at difficult flow conditions. Besides, jet in a crossflow case has a highly complicated flow domain which should be examined using numerical or experimental methods. In this study, numerical methods are used. The thesis consists of two main sections. In the first section, a validation study is conducted for numerical simulation method using experimental results of a generic missile geometry with lateral jet from literature. First, grid independency and turbulence model studies are conducted for validation model. In the turbulence model study k- Realizable and k- SST turbulence models have been used and results show that, k- Realizable model results in closer results to the experimental data. Moreover, surface pressure distribution data from experiment is used for validating numerical simulation method. Hence, results of the numerical simulation are in a good agreement with the experimental results except for some deviations at the recirculation region. In the second section, a parametric study is conducted for generating a database of jet and crossflow interactions using the validated numerical simulation method. In the parametric study, a slender missile geometry with lateral jet is used. Examined parameters are jet location, jet spouting angle, free-stream and jet flow velocity, and incidence angle. It is seen that, spouting jet normally results in best maneuverability. Furthermore, jet locations result in varying performance depending on the free-stream flow velocity. Once for all, jet flow Mach is inspected and seen that, jet performance depends strongly on jet flow Mach number.