Radiative Heating Uncertainty for Hyperbolic Earth Entry, Part 2: Comparisons with 1960s-Era Shock-Tube Measurements

摘要

The computational technique and uncertainty analysis presented in Part 1 (Johnston et al., "Assessment of Radiative Heating Uncertainty for Hyperbolic Earth Entry Part 1: Flight Simulation Modeling and Uncertainty," Journal of Spacecraft and Rockets, Vol. 50, No. 1,2013, pp. 19—38.) for Mars-return radiative heating simulations are applied to 1960s era shock-tube and constricted-arc experimental cases. It is shown that these experiments contain shock-layer temperatures and radiative flux values relevant to the Mars-return cases of present interest. Comparisons between the predictions and measurements, accounting for the uncertainty in both, are made for a range of experiments. A measure of comparison quality is defined, which consists of the percent overlap of the predicted uncertainty bar with the corresponding measurement uncertainty bar. For nearly all cases, this percent overlap is greater than zero, and for most of the higher temperature cases (T > 13,000 K), it is greater than 50%. These favorable comparisons provide evidence that the baseline computational technique and uncertainty analysis presented in Part 1 are adequate for Mars-return simulations.