In this study, modification of DSMC solver, called DsmcFoam, is presented for the simulation of rarefied hypersonic flow over re-entry vehicles with emphasis on the effect of counter flow jet. The DsmcFoam amendment includes implementation of VSS collision model for more accurate collision modelling, Non-uniform initial condition adjustment for improved convergence, Local Knudsen number post-processing for adaptive grid generation, and non-uniform boundary condition adjustment with different gas species for multi-gas flow interaction simulations. Therefore, the effect of counter flow jet on the vehicle aerodynamics and aerothermodynamics can be investigated. New validation test cases from VKF tunnel data of Apollo and blunt-cone re-entry geometries are compared to DsmcFoam which the results are in suitable agreement with experimental data and also MONACO code results. The major effect of counter flow jet is changing of bow shock configuration and its distance from the vehicle. Consequently, it is observed that increasing counter flow jet velocity or density causes reduction of the drag coefficient and heat flux on the vehicle. Also, variation of the velocity or density of counter flow jet leads to different jet-flow interaction patterns.

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