Shock-Wave Boundary-Layer Interaction (SWBLI) around open Flaps of EXPERT Capsule and their Consideration on Heat and Mechanical Loads under critical Re-Entry Flow Conditions
- Paper number
IAC-06-D2.5.02
- Author
Dr. Ognjan Bozic, German Aerospace Center, Germany
- Coauthor
Dr. José Longo, German Aerospace Center (DLR), Germany
- Year
2006
- Abstract
The primary objective of the ESA Project EXPERT is (1) to provide with a test-bed for the validation of aerothermodynamics physical-models, codes and ground test facilities in a representative flight environment; (2) to improve the understanding of issues related to analysis, testing and extrapolation to flight.
In the frame of EXPERT project DLR is proposing a flight experiment on shock-wave boundary-layer interaction (SWBLI) with shear-layer reattachment on control surfaces to improve our understanding about flap efficiency and corner/gap heating due to high temperature 3D effects, radiation-cooling effects, transition, turbulence (unsteadiness) and strong viscous hypersonic interaction. The present EXPERT payload shall consist of a passive and simple representative space-vehicle ceramic-flap with fixed actuator, equipped with reliable instrumentation. All flaps and flap components, like actuator and sensors housing will be designed and manufactured by MT Aerospace. The instrumentation of the flaps is responsibility of German Aerospace (DLR).
The objective of the present work is applying CFD to estimate for the most critical flight condition the maximal aerothermodynamic loads on the capsule surface, with a special emphasis on the flaps and their surrounding. The very important questions to be answered for the design of the flaps are the determination of the magnitude and location of the maximum temperatures with respect to the vehicle surface and its corresponding internal structure. The paper will also address the numerical design work to optimise a location of sensors in order to enhance the phenomena of interest.
The EXPERT capsule-geometry is available from the ESA-prime contractor. For the CFD solution a hybrid 3D grid with 25.6 million elements is created with the grid generator CENTAUR. Simulations of the 3D flow around the capsule configuration are here done with the DLR unstructured Navier-Stokes Code TAU. The selected flow conditions are Mach number 16.3, velocity 6.0 km/s, altitude 39.2 km. The flow is assumed in chemical non equilibrium condition, fully turbulent and the capsule surface as radiation-adiabatic (ε=0.85) with non catalytic as well as fully catalytic behaviour. Furthermore, the DLR HF3T code is used to determine the temperature changes at the capsules surface and its propagation inside the structure as a function of the trajectory parameters. The paper describes the features of this program also, its properties, limitations and discuss application results.
The CFD results for temperature, heat flux and surface pressure calculated for the selected critical flight condition show that the proposed concept for the instrumentation of both flaps and the capsule surfaces underneath the flaps is, in agreement with preliminary studies, technical feasible.
- Abstract document
- Manuscript document
IAC-06-D2.5.02.pdf (🔒 authorized access only).
To get the manuscript, please contact IAF Secretariat.