Nonequilibrium Stagnation Region Aerodynamic Heating of Hypersonic Glide Vehicles.

摘要

A simple method of predicting aerodynamic heating and corresponding radiation equilibrium surface temperature-time histories for critical locations on Space Shuttle Orbiter-type vehicles is presented. The method is based on a generalization of equations developed earlier by Rosner for predicting energy transfer and radiation equilibrium temperatures of surfaces with arbitrary catalytic activity and total emittance. Recent experimental data for O and N atom recombination probabilities on candidate material surfaces above 1000 K are used to assess chemical nonequilibrium effects for a range of nose radii and a specific Space Shuttle re-entry trajectory. Low catalytic activity will be especially important in locations of large effective nose radius by both increasing oxidation-resistant coating lifetime and reducing energy transfer into the vehicle.