As interest in hypersonic flight is once again growing, this is an opportune time to re-examine the applicability and limitations of our gasdynamic models. It is particularly important to address the flow regime between rarefied and continuum gasdynamics (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 Navier-Stokes method and a molecular simulation method to analyze an indented nose cone at hypersonic Mach numbers. The Navier-Stokes code is based on a finite-volume, explicit Runge-Kutta time-marching scheme. The molecular simulation method is based on the direct simulation Monte Carlo method. Theoretical and numerical differences between the two methods are discussed. Heat-transfer predictions are compared to experimental data.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering