Equilibrium, radiating viscous shock layer solutions are obtained for a number of trajectory points of the Fire II, Apollo 4, and PAET experimental flight vehicles. Convective heating rates calculated by a benchmark code agree well with two engineering correlations, except at high altitudes corresponding to low densities. Calculated radiation intensities are compared with the flight radiometer data and with inviscid flow results. Differences as great as 70% are observed between measured data and the viscous calculations. Because of boundary-layer absorption, viscous effects reduce the intensity to the wall by as much as 30% compared with inviscid intensities. Preliminary chemical and thermal nonequilibrium flow calculations along a stagnation streamline for a PAET trajectory predict an enhancement to the radiation owing to the chemical relaxation. Stagnation point solutions are also presented for future aeroassisted orbital transfer vehicle geometries with nose radii of 0.3-15 m.
Radiative Viscous Shock Layer Analysis of Fire, Apollo, and PAET Flight Data
Thermophysics ; 1985 ; Williamsburg, VA, United States
1986-01-01
Sonstige
Keine Angabe
Englisch
Planetary Atmosphere Experiments Test /PAET/
NTRS | 1971
PAET entry heating and heat protection experiment
AIAA | 1972
|PAET Entry Heating and Heat Protection Experiment
AIAA | 1973
|