Tobias Ecker, Jan Martinez Schramm , Leni Schmidt, Divek Surujhlal, Alexander Wagner
DOI Number XXX-YYY-ZZZ
Conference Number HiSST-2022-121
Ever since NASA’s X-plane program had developed demonstrators (X-15) pushing into the hypersonic high
altitude flight regimes, the effects of shock impingement and interference on local aerodynamic heating have
been a key issue for the design of hypersonic flight concepts. Currently DLR is involved in several flight
experiments, one of which is STORT which focuses on aerothermal loads on hot structures. One essential
structure flown on the STORT flight experiment is the fins experiment on the third stage. The fins were
investigated both on the vehicle, in windtunnels in Cologne and Göttingen but also numerically. For the
windtunnel experiment in the HEG (High Enthalpy Shock Tunnel Göttingen) the object of investigation is a
plate mounted fin which scales 1:2 to the flight hardware. The fin-induced shock boundary layer interaction
(SWBLI) on the plate leads to increased thermal loads. The heat flux on the flat plate and fin are investigated
using temperature sensitive paints (TSP). For the current study the flow on the plate and around the fin is
studied for two HEG freestream conditions at Mach 7.4 using RANS CFD. CFD calculations at both 0 deg
AoF and 15 deg AoF were performed and compared for flow topology and turbulence model influence. For 2
configurations first preliminary comparisons between experimental and CFD data were conducted. While
the XIII freestream condition compares well between experiment and CFD, the XV freestream condition
which shows clear signs of transitional flow exhibits rather complex physical phenomena which require
further investigation, both experimentally and numerically.