Abstract
Radiative heat may be greater than convective heat when flying at the velocity above 10 km/s. It is critical to precisely predict radiative heat for thermal protection system design. High-enthalpy flowfield solving and gas species’ radiant coefficient calculation are two main contents in computing radiation heat. A series of tests to obtain quantitative emission spectral radiation of air at high velocity have been conducted in a detonation-driven shock tube. Based on optical calibration and measurement, volumetric spectral radiant intensities of N2 and air have been acquired in the spectrum range of 310–380 nm and in the velocity range of 5.5–8 km/s. Unsteady non-equilibrium Navier-Stokes equations were numerically solved for temperature and gas concentration in the shock tube under test conditions. A narrowband model was used to calculate the gas spectral intensity at the specific position behind the shock corresponding to test time delay. The comparison between the computational results and the test measurement shows that the predictions of the flowfield parameters and the gas spectral radiation intensities are accurate and reliable.
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Acknowledgment
The authors gratefully acknowledge the support by the National Natural Science Foundation of China (Grant No.: 11402251).
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Lyu, J.M., Cheng, X.L., Yu, J.J., Li, F., Yu, X.L. (2019). Spectral Radiant Intensity Calculation of Air in Shock Tube. In: Sasoh, A., Aoki, T., Katayama, M. (eds) 31st International Symposium on Shock Waves 1. ISSW 2017. Springer, Cham. https://doi.org/10.1007/978-3-319-91020-8_148
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DOI: https://doi.org/10.1007/978-3-319-91020-8_148
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