REENTRY HEATING EXPERIMENTS USING AN INDUCTION HEATED PLASMA

摘要

Reentry stagnation heat transfer simulation data obtained with an induction heated plasma stream are reported. Stagnation point heat flux was measured by immersing a 1. 5 in. (3.8 cm) diameter, water cooled calorimeter in a 100 ft/sec (30.5 m/sec), 32 000 Btu/lb (0.75x108 J/kg) nitrogen plasma stream at 1 atmosphere pressure. The data are shown to be in good agreement with existing reentry theory and data. Stagnation point conditions in these tests corresponded to flight velocities from 14 000 to 40 000 ft/sec (4300 to 12 000 m/sec), altitudes from 120 000 to 170 000 ft (37 000 to 52 000 m), and reentry body nose radii from 4 to 10 ft (1.2 to 3 m).