Numerical Simulation of Transpiration Cooling for a High-Speed Vehicle with Substructure

This paper presents a numerical model that assesses the effect of applying transpiration cooling to both outer wall and substructure high-speed flight vehicle. The porous impulse response analysis for evaluation (PIRATE) code has been extended validated account quasi-two-dimensional lateral heat conduction effects, thereby allowing more complex geometries. enables very fast calculations two-dimensional transient temperature transpiration-cooled thermal protection system suitable first-order systems studies. To solve solid substructure, PIRATE coupled with commercial finite element package COMSOL. modeling longer-duration effects integrated load over trajectory. Transpiration using helium coolant applied wing leading-edge an aluminum substructure. Carbon–carbon ceramic composite ultra-high-temperature Zirconium diboride are chosen as candidate materials. Results history space shuttle reentry trajectory obtained, showing can lead 35% reduction in peak 65% gradients.