Tool for Rapid Transient Transpiration Cooled Re-Entry Simulation - Dataset

This paper presents a numerical model intended for a system study of transpiration cooled thermal protection systems. The code PIRATE(Porous ImpulseResponse Analysis forTranspiration cooling Evaluation) enables rapid transient calculations for thermal protection systems of hypersonic flight vehicles. In the code, semi-empirical aerodynamic correlations are employed. However, the code could also be used by applying higher fidelity inputs from CFD calculations. The wall temperature distribution is calculated by utilising the thermal impulse and step responses of porous media, increasing the calculation speed significantly. A heat flux balance is considered for a one-dimensional porous material. The code is validated with experimental data of plasma wind tunnel tests and the SHEFEX II flight experiment. The transient heating of a flat plate model in a steady state flow condition in the L2K plasma wind tunnel is assessed for both un-cooled and transpiration cooled cases. The SHEFEX II flight simulation accounts for transient external flow conditions and is used to assess the downstream coolant film effect after the injection point. The trends of experimental surface temperature measurements are replicated well by the simulations. The predicted and measured temperatures are in good agreement and within a margin of 10 %