An assessment of computational uncertainties is presented for numerical methods used by NASA to predict laminar, convective aeroheating environments for Mars-entry vehicles. A survey was conducted of existing experimental heat transfer and shock-shape data for high-enthalpy reacting-gas CO2 flows, and five relevant test series were selected for comparison with predictions. Solutions were generated at the experimental test conditions using NASA state-of-the-art computational tools and compared with these data. The comparisons were evaluated to establish predictive uncertainties as a function of total enthalpy and to provide guidance for future experimental testing requirements to help lower these uncertainties.
Assessment of Laminar, Convective Aeroheating Prediction Uncertainties for Mars-Entry Vehicles
AIAA Thermophysics Conference ; 2011 ; Honolulu, HI, United States
Journal of Spacecraft and Rockets ; 50 , 1
2013-01-01
Sonstige
Keine Angabe
Englisch
Assessment of Laminar, Convective Aeroheating Prediction Uncertainties for Mars-Entry Vehicles
Online Contents | 2013
|Stagnation-Point Aeroheating Correlations for Mars Entry
AIAA | 2020
|