Experimental and Numerical Studies of Radiation Emission from High-Temperature Air Behind 10 km/s Shock Waves 912025
In order to estimate the exact heat transfer from shock-heated air to the re-entering space vehicles, one needs the accurate understanding of its radiative characteristics.
The 10 km/s shock waves are produced by a free-piston, double-diaphragm shock tube, and the total and spectral-resolved radiation intensities of the shocked air are observed by using an image converter camera and a pair of photomultipliers.
The numerical analysis is carried out for one-dimensional, steady hypersonic flows with non-equilibrium chemical reactions of hot air, including the evaluation of radiation intensity.
The double-peak characteristic of radiation intensity for the shock waves above 10 km/s and the time-lag of radiation peak for different wave length are experimentally observed and qualitatively reproduced in numerical simulation.
Citation: Honma, H. and Iizuka, H., "Experimental and Numerical Studies of Radiation Emission from High-Temperature Air Behind 10 km/s Shock Waves," SAE Technical Paper 912025, 1991, https://doi.org/10.4271/912025. Download Citation
Author(s):
Hiroki Honma, Hiroyuki Iizuka
Pages: 12
Event:
International Pacific Air & Space Technolgy Conference
ISSN:
0148-7191
e-ISSN:
2688-3627
Also in:
International Pacific Air and Space Technology Conference and 29th Aircraft Symposium Proceedings-P-246
Related Topics:
Spacecraft
Heat transfer
Radiation
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