摘要: Hypersonic systems experience extreme aerothermal heating that is exacerbated by laminar to turbulent boundary layer transition. Given the non-linearity and wide range of spatiotemporal scales, Direct Numerical Simulation (DNS) of... 展开 Hypersonic systems experience extreme aerothermal heating that is exacerbated by laminar to turbulent boundary layer transition. Given the non-linearity and wide range of spatiotemporal scales, Direct Numerical Simulation (DNS) of a turbulent boundary layer remains a research tool that is inappropriate for practical designer use. Uncertainty associated with modeling the turbulent boundary layer has led to inefficient thermal protection system design margins. The current work analyzes the performance of a range of different fidelity turbulence modeling approaches on an ogive with cooled walls ((T_(wall)/T(aw) = 0.35), a relatively high friction Reynolds number (Re_ τ ≈ 1400), and a hypersonic Mach number (M_∞ = 5). Specifically, the van Driest-II flat plate empirical method, the SST RANS model, the Spalart-Allmaras RANS model, the Baldwin-Lomax RANS model, an algebraic Wall Model Large Eddy Simulation, and an Implicit Large Eddy Simulation are studied. It is determined that the fairly cool walls and moderate friction Reynolds number nature of the case produce a wide range of predictions and thus uncertainties in calculated mean and fluctuating quantities from the different methods. This highlights the uncertainty modern hypersonic vehicle designers face using current tool sets when taking the effects of turbulence into account. 收起