Aerothermodynamic analysis of high-altitude space launcher with direct-simulation Monte Carlo method
Aerothermodynamics of space launchers operating at high altitudes (above 100 km) is characterized by complex physical processes that are related to the substantially higher air rarefaction with respect to lower altitudes. Consequently, the use of continuum methods to numerically simulate such flow conditions is questionable. In this study, the problem of proper assessment of the aerothermodynamic behavior of space launchers operating at high altitudes is analyzed considering Vega in its ascent flight, an actual space launcher that has already performed a number of successful flights.