Experimental Hypersonic Shock/Boundary-Layer Interaction Studies on a Flat Plate at Elevated Surface Temperature
Abstract
Shock wave/boundary layer (SWBLI) experiments in a hypersonic flow with highly cooled walls at varying wall-to-freestream temperature ratios were successfully carried out at the High Enthalpy Shock Tunnel Gottingen (HEG).In the scope of the activity a flat plate model was modified to accommodate an improved electrical surface heating technique and to realize an increased spatial density of surface-mounted transducers for surface heat flux and pressure measurements. The wind tunnel model was designed to reach up to 800 K which marks the limits of the high temperature instrumentation. A shock generator subsystem was designed to be installed above the flat plate model in order to generate an impinging a shock wave onto the heated flat plate surface. The generated shock interacts with an incoming turbulent boundary layer which was tripped to ensure a fully turbulent boundary layer in a repeatable way. The resultant SWBLI was visualized with conventional and focused schlieren optical diagnostics. Results show that an increasing impinging shock angle increases the size of the separation region, which is in accordance with the accompanied LES results conducted by the group of Prof. Johan Larsson (Uni Maryland). The effect of varying wall-to-freestream temperatures were investigated in a range of Tw=Tinf = 1.14 to Tw=Tinf = 2.70 keeping the free-stream conditions constant while varying the surface temperature of the wind tunnel model. An increasing wall temperature was found to lead to an increased SWBLI interaction length. Furthermore, an impact on the surface heat flux relaxation after the shock impingement was observed.
Document Details
- Document Type
- Technical Report
- Publication Date
- Mar 02, 2022
- Accession Number
- AD1165521
Entities
People
- Alexander Wagner
Organizations
- German Aerospace Center