L. Bussler, S. Karl, M. Sippel

DOI Number XXX-YYY-ZZZ

Conference Number HiSST-2022-0420

The booster stage of SpaceLiner is a winged, reusable first stage launching vertically and landing
horizontally. With a separation Mach number of around 13 at an altitude of approximately 70 km, it
flies through regimes from hypersonic to subsonic along its descent trajectory. All of these flight regimes
are relevant in the frame of the analysis of its design based on the occurring mechanical and thermal
loads. One aspect present in the hypersonic flight regime and identified as potentially critical is the
shock-shock interference. The shock wave originating at the fuselage nose hits the leading-edge of the
wing and interferes with the wing leading-edge shock. This leads to a local increase in both pressure
and heat flux within the region of shock-shock interference. The increased heat flux might go beyond
thermal protection system limits and lead to severe damage of the reusable first stage. The primary
objective of this paper is to quantify the heat flux increase due to shock-shock interference in the area
of the wing leading-edge. Furthermore, to assess if the feasibility of SpaceLiner booster is put in
question by the phenomenon of shock-shock interference. And finally, to determine whether fixed wing
design options for SpaceLiner Booster are still viable despite shock-shock interference.

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In Categories: 1.Events, HiSST 2022
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