On linear stability analyses of hypersonic laminar separated flows in a DSMC framework part I: Base flow computations in a double cone and a 'tick' model

Unsteadiness of a shock dominated hypersonic flow including shock wave boundary layer interactions and flow separation over a double cone and 'tick' configurations are investigated. The time accurate DSMC solutions combined with global linear stability and the residuals algorithm provide an opportunity to predict the corresponding steady state solution at a fraction of the DSMC simulation cost and provide a theoretical basis for the assessment of the steady state condition. It is observed that the time required to reach steady state is conditioned by the separation region and the shock wave boundary layer interaction.