Ceramic Matrix Composite Materials for Transpiration Cooling

The proposed effort will formulate and demonstrate the methodology for fabricating Porous Ceramic Matrix Composite (PCMC) transpiration plates with controlled levels of porosity, suitable for high-speed/high-temperature missile applications. The porosity of the fabricated plates will be characterized and compared with traditional porous metallic plates with drilled holes constructed for scramjet model tests in the CUBRC, Inc. shock tunnel facility. Thermal and mechanical testing of the PCMC plates will be performed for plates with varied levels of porosity. Testing will be performed at CUBRC at realistic hypersonic conditions where the CUBRC combustion duct model will be fitted with the PCMC transpiration plates and comparison will be made to the detailed experimental and CFD studies that have been performed using traditional transpiration plates.