A comparison of navier-stokes and monte carlo methods for hypersonic flows

As interest in hypersonic flight is once again growing, this is an opportune time to re-examine the applicability and limitations of our gas dynamic models. It is particularly important to address the flow regime between non-continuum and continuum gas dynamics (the slip or transitional regime) because these flows may be common on future hypersonic vehicles and they are very poorly understood. This paper uses a full NavierStokes method and a molecular simulation method to analyze an indented nose cone at hypersonic Mach numbers. The Navier-Stokes code is based upon a finite-volume, explicit Runge-Kutta time-marching scheme. The molecular simulation method is based on the Direct Simulation Monte Carlo (DSMC) method. Theoretical and numerical differences between the two methods are discussed. Heat transfer predictions are compared to experimental data.