Abstract
This article presents the full operational experimental capabilities of the plasma wind tunnel facilities at the Institute of Space Systems at the University of Stuttgart. The simulation of the aerothermodynamic environment experienced by vehicles entering the atmosphere of Earth is attempted using three different facilities. Utilizing the three different facilities, the recent improvements enable a unique range of flow conditions in relation to other known facilities. Recent performance optimisations are highlighted in this article. Based on the experimental conditions demonstrated a corresponding flight scenario is derived using a ground-to-flight extrapolation approach based on local mass-specific enthalpy, total pressure and boundary layer edge velocity gradient. This shows that the three facilities cover the challenging parts of the aerothermodynamics along the entry trajectory from Low Earth Orbit. Furthermore, the more challenging conditions arising during interplanetary return at altitudes above 70 km are as well covered.
Highlights
State-of-the-art experimental investigations of atmospheric entry flight are conducted using impulse facilities or plasma wind tunnels [36]
New arcjet facilities have been developed at the China Aerodynamics Research and Development Center (CARDC)
We only present measured flow conditions to provide a profound base for the performance of the facilities
Summary
State-of-the-art experimental investigations of atmospheric entry flight are conducted using impulse facilities or plasma wind tunnels [36]. New plasma generator developments were mainly driven by the requirements for higher enthalpy levels and higher total pressures for atmospheric entry from interplanetary travel. This graph is not plotted based on actual measurement data. We only present measured flow conditions to provide a profound base for the performance of the facilities. This paper focuses on the presentation of the recent performance analysis of the facilities developed at the Institute of Space Systems (IRS) and the associated capabilities for the investigation of entry manoeuvres in the atmospheres of Earth. Assessment of high enthalpy flow conditions for re‐entry aerothermodynamics in the plasma
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