Isosurfaces showing q-criterion from a LES computation of the RFZ model during the aerodynamic glide phase (backwards flight) at a Mach number of 0.85.
In recent years, controllable first stages have emerged as the most promising concept for reusable launch vehicles (RLVs), thanks in no small part to the commercial success of the SpaceX Falcon 9 rocket. These first stages can autonomously return to the launch site after multiple deceleration maneuvers (retro-propulsion). This approach is now being pursued by other spacefaring nations and holds the potential for significant cost savings in future launch systems. Numerical methods for flow simulation are essential when designing these vehicles, as many maneuvers must be executed at high speeds, subjecting the rocket to considerable thermal and mechanical stresses. Unfortunately, numerical and experimental reference data for this application are lacking, hindering the validation of simulation-based methods and the comparison of different codes. Aerospace engineers currently have access to a range of well-studied and standardized reference configurations for conventional aircraft, but such resources are lacking for reusable spacecraft.
The project of the DLR Institute of Aerodynamics and Flow Technology aims to fill this gap by providing the research community with an open-source model of an RLV. This facilitates a collaborative approach to exploring the challenges associated with RLV development. Until now, there have been limited studies on phenomena such as surface heating, vehicle aerodynamics during reentry and glide phases, interaction of exhaust jets with each other and with the structure, as well as stability and control. The intention is for this model to serve as a consistent validation case, promoting collaboration with international research institutions and providing a broader literature base for the development of future spacecraft.
