AMES RESEARCH CENTER, Calif. - The Ames Entry Heating was designed to test ablative heat shield materials under combined convective and radiative heating.
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Background: AMES RESEARCH CENTER, Calif. - The Ames Entry Heating was designed to test ablative heat shield materials under combined convective and radiative heating. It is capable of simulating the convective and radiative heating for the Apollo mission.
The convective flux is supplied by an arc-type air heater shown on the left and in conjunction with a supersonic nozzle (M-4) and an exhaust system. The radiative flux is supplied by a carbon arc lamp shown on the right and in conjunction with two large ellipsoidal mirrors. The carbon arc is positioned at the focal point of the mirror ON the right end and reimaged by the mirror on the left end onto the nose of the model.
For these movies of the Mercury capsul reentering the atmosphere, only the convective heating is used. Vehicles reentering at satellite speed will not experience much, if any, radiative heating from the shock layer. The facility is capable of simulating the convective heating rate at the stagnation point of the Mercury capsule (approximately 100 Btu/ft2sec). It is not capable of simulating the Mach number, Reynolds number or Enthalpy (tests were made at an enthalpy of 4000 Btu/lb). The surface temperature of the char layer is estimated to be 3100oF.
The model in sequences is 1 1/2-inch diameter and is constructed of an aluminum body with a phenolic resin plus fiberglass heat shield. An all steel retro pack is mounted on the front. At the end of the 25-second test, the retro pack has completely disappeared.