AM06-15-005 火星大気を模擬した気体中を伝播する極超音速衝撃波背後の温度解析(空気力学・高エンタルピー流(1),一般講演)

概要

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Spectroscopic measurements were conducted in a Martian type atmosphere (97% of CO_2, 3% of N_2). To simulate the entry condition into Martian aerosphere, a single-stage free-piston shock tube was used to produce shock wave velocity of almost 5.3km/s in a Martian type atmosphere. A spectrograph equipped with an ICCD camera was used to obtain radiation spectral data behind the shock waves propagating in the Martian type atmosphere. From the spectroscopic experimental results, the dominant molecular spectrum was turned out to be the CN. Applying the "Rankine-Hugoniot equation" and "Boltzmann plot method" to the CN Violet(Δυ=0) band and the C_2 Swan(Δυ=0) band, which was dominant and typical spectrum bands behind the shock wave propagating in Martian type atmosphere, we were able to obtain the vibrational temperature T_υ, at the point of 2.0mm behind the shock front. It turned out to be T_υ=10700±800K at that point.
日本流体力学会の論文
2006-09-05