PRELIMINARY COMPUTATIONAL INVESTIGATION ON AERODYNAMIC PHENOMENA ON DELFT AEROSPACE RE-ENTRY TEST VEHICLE

摘要

Computations of a hypersonic Mach 18 laminar flow around two different re-entry models at flow conditions where maximum stagnation heat flux occurs are presented. The computational investigation is within the framework of the DART-demonstrator program (Delft Aerospace Re-entry Test demonstrator) of the Faculty of Aerospace Engineering in Delft. During its re-entry flight the DART program will cover measurements of important aerodynamic phenomena, in particular separation and reattachment in the hypersonic flight regime. The present computational results show that the intended separation-reattachment region is larger for the REVolution shape (a blunted cone-flare combination) than for the Volan shape (a blunted cylinder-flare combination) (see Figure 1) and therefore the REVolution shape is more suitable for this study. However, computed heat fluxes of both models show higher thermal loads on the REVolution flare than the super alloy PM1000 is able to cope with, while the heat flux on the Volan flare are lower than the permitted value.