@inproceedings{oai:jaxa.repo.nii.ac.jp:00004133,
 author = {山田, 剛治 and 吾郷, 祥太 and 久保, 優斗 and 松野, 隆 and 川添, 博光 and Yamada, Gouji and Ago, Shota and Kubo, Yuto and Matsuno, Takashi and Kawazoe, Hiromitsu},
 book = {宇宙航空研究開発機構特別資料, JAXA Special Publication},
 month = {Nov},
 note = {5th Symposium on Integrating CFD and Experiments in Aerodynamics (October 3-5, 2012, Chofu Aerospace Center, Japan Aerospace Exploration Agency (JAXA)), Chofu, Tokyo, Japan, In this study, shock layer radiation is investigated by experimental and numerical approach. Radiation profiles of N2, N2(+), and N are observed in two test conditions of initial pressure and velocity by time-resolved emission spectroscopy. Flow properties behind shock front are computed by the CFD code with two-temperature thermochemical model. The results are used as inputs for the radiation analysis code “SPRADIAN 2” to derive the radiation profiles behind shock front along the line of sight. Comparison between experiments and calculations shows that the decline of calculated radiation intensity is slower than that of measured one.Therefore, the present calculation fails to reproduce the measured radiation profile. This is considered to be due to the fact that the two-temperature model seems to lose its accuracy in the intermediate hypersonic flow regime. Further investigations are necessary to improve the accuracy of the two-temperature model., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0062070025, レポート番号: JAXA-SP-13-001E},
 pages = {307--315},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {Experimental and Numerical Study on Shock Layer Radiation for Planetary Entry Flights},
 volume = {JAXA-SP-13-001E},
 year = {2013}
}