Flow Characterization at Heated Air Supersonic Facility SBR-50

The supersonic wind tunnel facility SBR-50 at the University of Notre Dame was built in 2015 for experimental research related to shock wave (SW) interactions with obstacles and boundary layers (BL) as well combustion a plasma-based flow control. Currently, provides following range parameters test section area nozzle exit 76.2 × mm: Mach number M=2 4, total pressure p0= 1–4 bar, stagnation temperature T0= 300–775 K, typical duration steady-state t= 0.5–2 s. One distinct feature is Ohmic gas heater installed long plenum section. Objective this study characterize facility, specifically dynamics temperature. Two measuring methods were applied collection detailed dataset: thermocouple measurements schlieren-based thermal mark (laser spark) velocimetry. data are compared 3D Navier–Stokes modelling over entire flowpath. Particularly, proves that original schematics (the concept virtual piston plenum) allow longer operation constant volume adiabatic cooling stored gas.