6 research outputs found

    Stagnation Point Heat Transfer with Gas Injection Cooling

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    The present paper deals with an experimental study of the stagnation-point heat transfer to a cooled copper surface with gas injection under subsonic conditions. Test were made with a probe that combined a steady-state water-cooled calorimeter that allows the capability to study convective blockage and to perform heat transfer measurements in presence of gas injection in the stagnation region. The copper probe was pierced by 52 holes, representing 2.4% of the total probe surface. The 1.2 MW high enthalpy plasma wind tunnel was operated at anode powers between 130 and 230 kW and a static pressures from 35 hPa up to 200 hPa. Air, carbon dioxide and argon were injected in the mass flow range 0-0.4 g/s in the boundary layer developed around the 50 mm diameter probe. The measured stagnation-point heat transfer rates are reported and discussed

    Experimental analysis of the interaction of carbon and silicon ablation products with expanding hypersonic flows

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    Thermal protection is required for vehicles entering planetary atmospheres to protect against the severe heating loads experienced. Characterization of candidate materials is often done utilizing plasma or arc-jet facilities, which provide steady-state testing of the thermal environments experienced during hypersonic flight, but do not correctly simulate hypersonic flowfields. Conversely, impulse facilities can reproduce flight velocities and enthalpies but have extremely short test times, prohibiting testing of thermal response. To better understand how these materials interact with hypersonic flows, experiments were conducted at the X2 expansion tunnel at the University of Queensland. Preheated strips of carbon-carbon and silicon carbide-coated carbon-carbon were mounted in a two-dimensional compression wedge and tested in Earth entry flow, marking the first time silicon carbide has been investigated in this facility. Calibrated spectral measurements were obtained in the near-stagnation and expansion regions for surface temperatures from 1900 K to 2600 K. Cyanogen emissions dominated while atomic silicon and dicarbon were also observed. Emissions for both materials displayed a similar increase near the wall, while emissions for silicon carbide-coated samples displayed a distinct rise downstream of the shock, which suggests a higher concentration of ablative species resulting from a higher ablation rate

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