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Please use this identifier to cite or link to this item: http://hdl.handle.net/11133/2783

Title: C/Cコンポジットの炭酸ガスプラズマ気流中の耐熱実験
Other Titles: C/C コンポジット ノ タンサンガス プラズマ キリュウチュウ ノ タイネツ ジッケン
Thermal protection testing for C/C composite in carbon dioxide plasma flow
Authors: 北川, 一敬
KITAGAWA, Kazutaka
Issue Date: 30-Sep-2013
Publisher: 愛知工業大学
Abstract: Arc heated wind tunnel facility was conducted a high enthalpy and hypersonic flow wluch are used to investigate for purposes as thermal protective testing of reentry flow into the other planet. The emission spectra profiles in shock layer of the ablation materials are spectroscopically measured for C02 arc plasma flow. Vibrational temperature obtained from Boltzmann plot method for C2 SWAN at 20mm upstream of the sonic throat and shock layer in bow shock around the blunt body. The d3Πg -a3Πu transition ofΔν=O of C2 SWAN, is referred from 509 to 516 nm. Vibrational temperature is determined to be 2700 K of C/C Composite from band head ratio of incline to (0,0) -(2,2) of the C2 SWAN band system emission.
URI: http://hdl.handle.net/11133/2783
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