Numerical investigations on the aerodynamics of Shefex-III Launcher

Abstract The present work is a numerical study of the aerodynamic problems related to the hot stage separation of a multistage rocket. The adapter between the first and the second stage of the rocket uses a lattice structure to vent the plume from the 2nd-stage-motor during the staging. The lattice structure acts as an axisymmetric cavity on the rocket and can affect the flight performance. To quantify the effects, the DLR CFD code, TAU, is applied to study the aerodynamic characteristics of the rocket. The CFD code is also used to simulate the start-up transients of the 2nd-stage-motor. Different plume deflectors are also investigated with the CFD techniques. For the CFD computation in this work, a 2-species-calorically-perfect-gas-model without chemical reactions is selected for modeling the rocket plume, which is a compromise between the demands of accuracy and efficiency.