CFD analysis of missile shroud separation

Çeliker, Hasan Erkan
In this thesis, shroud separation on generic missile is performed by using the Computational Fluid Dynamics (CFD). This study is divided into two main parts. In the first part, aerodynamic coefficients of generic missile are calculated and store separation is performed. Additionally, the numerical analyses results are compared respectively with the experimental results in order to validate of CFD analyses method. Three-dimensional steady/unsteady Navier-Stokes equations are solved and three different turbulence models which are one-equation Spalart-Allmaras, two-equation Realizable k-ε, and two-equation k-ω SST methods are used. Aerodynamic coefficients results are validated with a HB generic missile and multi body dynamic simulation is validated with an EGLIN store separation test case by using Chimera grid method. Aerodynamic coefficients and store position/angle changes results are compared with experimental data respectively and all of them are in good agreement. As a result of all this validation, in the second part, a parametric study for shroud separations on generic missile is carried out in order to investigate altitude, Mach number, angle of attack, side-slip angle and ejection moment effects during the separation, and results of CFD simulation are presented.
Citation Formats
H. E. Çeliker, “CFD analysis of missile shroud separation,” M.S. - Master of Science, Middle East Technical University, 2015.