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S8 Engenharia Aeroespacial |
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Title:
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EXPERIMENTAL HEAT TRANSFER AND PRESSURE INVESTIGATIONS OF "DOUBLE APOLLO
DISC" INLET AT MACH 10
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Summary :
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ABSTRACT. "APOLLO COMMAND MODULE S" LOWER HEAT SHIELD CONFIGURATION WAS TESTED IN THE RPI 24-IN. DIAMETER HYPERSONIC SHOCK TUNNEL (RPI-HST). A 6-IN. DIAMETER ALUMINUM "DOUBLE APOLLO DISC" MODEL WAS FABRICATED AND FITTED WITH THE THIN-FILM PLATINUM HEAT GAUGES AND PIEZOELECTRIC PRESSURE TRANSDUCERS OVER ITS FOREBODY SURFACE. FREESTREAM MACH 10 FLOW, WITH A STAGNATION TEMPERATURE OF 800 K, WAS SELECTED TO CONDUCT THE HEAT TRANSFER AND PRESSURE MEASUREMENTS OVER THE "DOUBLE APOLLO DISC" MODEL. WHEN THE BARE 6-IN. DIAMETER "DOUBLE APOLLO DISC" MODEL WAS TESTED, THE HEAT TRANSFER, THE PRESSURE RATIO MEASUREMENTS AND THE SCHLIEREN PHOTOGRAPHS OF THE SHOCK STRUCTURE WERE FOUND TO BE QUALITATIVELY SIMILAR TO PRIOR EXPERIMENTAL AND THEORETICAL RESULTS.
KEYWORDS: HYPERSONIC FLOWS, EXPERIMENTAL HEAT TRANSFER MEASUREMENTS, EXPERIMENTAL PRESSURE MEASUREMENTS, BLUNT BODY
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Author :
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Minucci, Marco A.S
Myrabo, Leik N,
Nagamatsu, Henry T.
Toro, Paulo G. de P.
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Paper View :
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COBEM99
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