Extrapolating Aero Data from a Demonstrator to an Operational Vehicle

Abstract

The study presents a numerical investigation for the SPHYNX re-entry vehicle performed by DLR under ESA contract. The current aero- and aero- thermodynamic study is carried out based on the solutions of the stationary Navier-Stokes equations. Several flow conditions derived from the flight trajectory are considered, in particular the portion comprised from 85 Km to 60 Km altitudes, i.e. Mach numbers from 28 to 14. All Navier-Stokes simulations are carried out for chemical non-equilibrium under laminar conditions. Fully and partially catalytic wall conditions are considered. The numerical solutions are assessed by grid convergence analysis and comparing the present data with available results for the X-38 vehicle. The study provides first positive evidences about the possibility to use an existing aerodynamic and/or aero-thermodynamic database to design a downsized or upsized vehicle which shall fly a different re-entry trajectory. Thus a verification of the applicability of X38 aerodynamic and aerothermodynamic databases is highlighted.