Trajectory-Based Validation of the Shuttle Heating Environment

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Abstract
Chemically reacting, three-dimensional, full Navier-Stokes calculations are generated around the shuttle orbiter and are compared with the STS-2 Right database at eight trajectory locations. Numerical estimates of quantities necessary for thermal protection system design, surface temperature and heating profiles, integrated heat load, bond-line temperatures, and thermal protection system thicknesses are compared with the STS-2 shuttle data. The effects of surface kinetics, turbulence, and grid resolution are investigated. It is concluded that trajectory-based thermal protection system sizing, the use of a Navier-Stokes flow solver combined with a conduction analysis applied over an entry trajectory, is a beneficial tool for future thermal protection system design. This conclusion is based on a reasonable agreement between the flight data and numerical predictions of surface heat transfer and temperature profiles, integrated heat loads and bond-line temperatures at most of the wind-side thermocouples. The effects of turbulent heating on thermal protection system design are illustrated. For future large entry vehicles, it is concluded that the prediction of turbulent transition will be a major driver in the thermal protection system design process. Finally, one potential payoff of using trajectory-based thermal protection system sizing, a reduction in thermal protection system mass, is illustrated.

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