Non-premixed supersonic combustion modelling with aerothermal consistency

In supersonic combustion, a key modelling challenge arises from the nonlinear coupling between the aerodynamic heat and heat from chemical reaction. In the present work, an aerothermo-consistent (ATC) flamelet model is newly proposed to take into account this issue, along with a pressure scaling to incorporate the chemical influence from gaseous compressibility. In addition, from the aerodynamic relation, a new manifold entry parameter ΔT is introduced to represent the temperature variation induced by aerodynamic heating/cooling. The aerothermal consistency of all the involved parameters can be ensured by the pre-tabulation procedure and a well designed iteration algorithm, preserving the computational efficiency of flamelet methods. Results from the proposed model demonstrate good agreement with those of the direct integration of finite-rate chemistry (DIC). Various flow configurations and fuels have been tested, confirming its potential as a reliable and efficient tool for supersonic combustion simulations.