An investigation is undertaken into the potential use of carbon-carbon materials for Scramjet combustors and configurations utilising regenerative and radiative cooling are considered. The analysis uses the ANSYS package to couple a CFD analysis of the fuel cooling with a structural thermal analysis. One sample result is also compared with numerical analysis. One of the variations investigated was the value of the thermal conductivity of the carbon-carbon as the values for this found in the literature vary greatly. Examples using high and low thermal conductivity are computed showing the resulting difference in temperatures. The results show that for a representative Mach 8 Scramjet flight a thermal equilibrium is achievable whilst keeping the maximum temperatures within the limits of the material. Copyright
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