Abstract
made of glass ceramics. The thickness of TSP layer was varied from 0.2 to 3 µm. The models were tested at Mach 10 in the JAXA 0.44-m Hypersonic Shock Tunnel and heat flux caused by aerodynamic heating on the model surface was measured. A comparison between TSP data and conventional thermocouple data showed that the measurement error changed with the layer thickness in nonlinear fashion. In addition, the difference between TSP and thermocouple measurement was larger than theoretical prediction. For TSP layer thickness less than 0.5µm, the accuracy in heat flux measurement by TSP was within the uncertainty of conventional thin thermocouple measurement. To demonstrate the capability of TSP with the optimized thickness, tests using a 3-dimensional wing-body model have been conducted and the complicated heat flux pattern caused by shock-wave/shock-wave interaction has been observed.
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