日本航空宇宙学会誌
Online ISSN : 2424-1369
Print ISSN : 0021-4663
ISSN-L : 0021-4663
極超音速飛行体周りに形成される非平衡衝撃波層からの輻射熱伝達に関する実験及び解析
小紫 公也笠原 次郎矢野 修二郎藤原 俊隆
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ジャーナル フリー

1994 年 42 巻 487 号 p. 503-509

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Radiative heat transfer from the strong shock layer generated around a hypersonic flight model is experimentally investigated by using a ballistic range (two-stage light-gas gun). A plastic projectile of 1.2cm diameter is accelerated in this facility up to 5.3km/s (M=15), and the radiation spectra and global power emission from the projectile are measured. As a result, radiation spectra from some carbon-containing molecules such as CN and CO, were observed along with the air spectra, and the radiative heat transfer rate was estimated. Since the projectile launched in a ballistic range is two orders of magnitude smaller than the actual space vehicles, the model-dimension effect on shock layer structure is examined by analytical and numerical considerations, and a scaling law has been developed. Radiative heat transfer rate around a projectile was calculated, and the validity of conventional numerical model is discussed by comparing the computed result with the measured one.

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© The Japan Society for Aeronautical and Space Sciences
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