NUMERICAL ANALYSIS OF THE AERODYNAMIC PERFORMANCE OF THE ROCKET ENGINE S-30 COUPLED TO A SCRAMJET DEMONSTRATOR
scramjet, VS-30, shock wave - boundary layer interactions, hypersonic flow
In this work we analyze the effect of the coupling of a Scramjet demonstrator in a Brazilian rocket engine, the VS-30 rocket, in terms of a numerical investigation of the flow along the fuselage geometry. We consider local aspects of the flow and the comparison of global flow parameters, namely the pressure distribution and the wall shear stress, for both geometries. The reference geometry of the rocket engine consists of a solid propulsion suborbital vehicle, while the Scramjet geometry was designed to be operated at flight conditions of Mach 5.79 and an altitude of 20 km. A set of 2D axisymmetric and planar numerical domains were generated for both geometries. We consider steady-state conditions in all cases, and for the modelling of turbulence, the transition k-kl-ω viscous model was used. The numerical simulations were able to capture the theoretically expected oblique shock and expansions waves that usually occur in the flow in these types of geometries. Local effects in the flow were observed such as the emergence of recirculation zones and hydrodynamic flow instabilities related to the interactions between the shock waves and the wall boundary layer. In addition, the aerodynamic drag forces, both drag and pressure, were quantified. We show that the Scramjet demonstrator coupled in the VS-30 can lead to an increase in 6,53% of the total drag on the vehicle, such increase can cause considerable deviations in the nominal trajectory of the VS-30 rocket.