Aero-Thermodynamic Analysis of Expert Capuslereentry Vehicle Using CFD

The main task of the project is the evaluation of the Aero-thermodynamic analysis of reentry trajectory. Computational fluid-dynamics results are presented to show the flow field around a blunted coneflare in hypersonic flow. This problem is of particular interest since it features most of the aspects of the hypersonic flow around planetary entry vehicles. The region between the cone and the flare is particularly critical with respect to the evaluation of the surface heat flux. Indeed, flow separation is induced by the shock wave boundary layer interaction, with subsequent flow reattachment, that can dramatically enhance the surface heat transfer. The exact determination of the extension of the recirculation zone is a particularly delicate task for numerical codes. A numerical approach has been adopted to study the flow field that develops around the EXPERTS capsule. Laminar flow computations have been carried out using a full NavierStokes solver, with free stream condition with two different Mach number. A simplified dissociative model based on the Monti-Napolitano method has been implemented into the commercial CFD code FLUENT. The CFD solution is abating to study the 3D flow filed around the EXPERTS capsule. The results and description performed as for the results obtained by the numerical solution.