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报告编号NASA-CR-141534, DMS-DR-2166
来源IDNTRS_Document_ID: 19750018974
Heat transfer tests of an 0.006-scale thin-skin space shuttle thermocouple model (41-OTS) in the Langley Research Center unitary plan wind tunnel at M equals 3.7 (IH16)
Walstad, D. G.
英文摘要The results are presented of supersonic heat transfer tests performed on the .006 scale space shuttle vehicle model (41-OTS) in the Langley Research Center Unitary Plan Wind Tunnel. These tests were conducted to parametrically investigate ascent heating of the integrated vehicle and its components. The tests were conducted at a nominal Mach number of 3.7 and Reynolds numbers per foot of 2 and 5 million. The model configurations investigated were the integrated vehicle and each component alone (i.e. orbiter, tank and SRB). All the configurations were run with and without transition strips and through an angle of attack range of 0 deg to minus 5 deg with the exception of the SRB which was tested through an angle of attack range of minus 5 deg to 90 deg. The heat transfer data were obtained from 223 iron constantan thermocouples attached to stainless steel thin-skin areas of the model.
英文关键词SPACE SHUTTLE ASCENT STAGE SPACE SHUTTLES SUPERSONIC HEAT TRANSFER WIND TUNNEL TESTS AERODYNAMIC HEATING EXTERNAL TANKS GRAPHS (CHARTS) SPACE SHUTTLE BOOSTERS SPACECRAFT CONFIGURATIONS SPACECRAFT MODELS SUPERSONIC SPEED TABLES (DATA) THERMOCOUPLES
出版年1975
报告类型Technical Report
语种英语
国家美国
URLhttp://hdl.handle.net/2060/19750018974
资源类型科技报告
条目标识符http://119.78.100.177/qdio/handle/2XILL650/258607
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GB/T 7714
Walstad, D. G.. Heat transfer tests of an 0.006-scale thin-skin space shuttle thermocouple model (41-OTS) in the Langley Research Center unitary plan wind tunnel at M equals 3.7 (IH16),1975.
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