Temperature determination in a shock tube using hydroxyl radical A-X band emission
Author:
Affiliation:
1. Department of Aerospace Engineering, Korea Advanced Institute of Science and Technology, 291 Daehak-ro, Daejeon 34141, South Korea
2. Department of Aerospace System Engineering, Sejong University, 209 Neungdong-ro, Seoul 05006, South Korea
Funder
BK21 plus program
National Research Foundation of Korea
Publisher
AIP Publishing
Subject
Condensed Matter Physics,Fluid Flow and Transfer Processes,Mechanics of Materials,Computational Mechanics,Mechanical Engineering
Link
http://aip.scitation.org/doi/pdf/10.1063/1.5082240
Reference41 articles.
1. Shock-tube measurement of the rate constant for excited hydroxyl(A2.SIGMA.+) formation in the hydrogen-oxygen reaction
2. Validation of CO 4th positive radiation for Mars entry
3. Equilibrium Radiative Heating from 9.5 to 15.5 km/s for Earth Atmospheric Entry
4. Investigation of oxygen dissociation and vibrational relaxation at temperatures 4000–10 800 K
5. Oxygen Vibrational Relaxation Times: Shock Tube/Laser Absorption Measurements
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