Computational Fluid Dynamics for Winged Re-entry Vehicles at Hypersonic Conditions

摘要: The present work reviews the status of computational fluid dynamics methods for predicting hypersonic flow environments around winged re-entry vehicles. Special attention is paid to applicability current solvers use within context future aerothermodynamic shape optimization methods. Recent experiences using dynamic Columbia accident investigation and Shuttle Return Flight Program form basis assessment. Attention focused on real-gas Navier-Stokes appropriate regimes typically experienced by earth-entry Each major physical numerical modeling issues these examined individually: methods, thermodynamic properties, laminar transport mass, momentum energy, chemistry kinetics, gas-surface interaction modeling. variability uncertainty levels Navier- Stokes solvers, in terms mesh refinement choices, are explored different regions including, wind-side acreage, wing leading edges, lee sides, coves aft bodies. feasibility employing design entry vehicle shapes also addressed.