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Spectral Radiant Intensity Calculation of Air in Shock Tube

  • Jun Ming Lyu
  • X. L. Cheng
  • J. J. Yu
  • F. Li
  • X. L. Yu
Conference paper

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.

Notes

Acknowledgment

The authors gratefully acknowledge the support by the National Natural Science Foundation of China (Grant No.: 11402251).

References

  1. 1.
    J.D. Anderson, An engineering survey of radiating shock layers. AIAA J. 7(9), 1665–1675 (1969)CrossRefGoogle Scholar
  2. 2.
    G.E. Palmer et al., Direct coupling of the NEQAIR radiation and DPLR CFD codes. J. Spacecr. Rocket. 48(5), 836–845 (2011)CrossRefGoogle Scholar
  3. 3.
    D. Hash et al., FIRE II calculations for hypersonic nonequilibrium aerothermodynamics code verification: DPLR, LAURA, and US3D, in 45th AIAA Aerospace Sciences Meeting and Exhibit, p. 605 (2007)Google Scholar
  4. 4.
    D.L. Cauchon, Radiative Heating Results from the FIRE II Flight Experiment at a Reentry Velocity of 11.4 Kilometers per Second. NASA TM X-1402 (1967)Google Scholar
  5. 5.
    I.D. Boyd, P.M. Jenniskens, Modeling of stardust entry at high altitude, part 2: Radiation analysis. J. Spacecr. Rocket. 47(6), 901–909 (2010)CrossRefGoogle Scholar
  6. 6.
    S. Abe et al., Near-ultraviolet and visible spectroscopy of HAYABUSA spacecraft re-entry. Publ. Astron. Soc. Jpn. 63(5), 1011–1021 (2011)CrossRefGoogle Scholar
  7. 7.
    P. Reynier, Survey of high-enthalpy shock facilities in the perspective of radiation and chemical kinetics investigations. Prog. Aerosp. Sci. 85, 1–32 (2016)CrossRefGoogle Scholar
  8. 8.
    A.M. Brandis, B.A. Cruden, Benchmark EAST experiments for earth re-entry, in 55th AIAA Aerospace Sciences Meeting, p. 1145 (2017)Google Scholar
  9. 9.
    A.M. Brandis et al., Non-equilibrium radiation for earth entry, in 46th AIAA Thermophysics Conference, p. 3690 (2016)Google Scholar
  10. 10.
    S.W. Lewis et al., Expansion tunnel experiments of earth reentry flow with surface ablation. J. Spacecr. Rocket. 53(5), 887–899 (2016)CrossRefGoogle Scholar
  11. 11.
    H. Takayanagi, K. Fujita, Absolute radiation measurements behind strong shock wave in carbon dioxide flow for mars aerocapture missions, in 43rd AIAA Thermophysics Conference, p. 2744 (2012)Google Scholar
  12. 12.
    X. Lin et al., Measurements of non-equilibrium and equilibrium temperature behind a strong shock wave in simulated Martian atmosphere. Acta Mech. Sinica 28, 5 (2012)Google Scholar
  13. 13.
    C.O. Johnston, Nonequilibrium Shock-Layer Radiative Heating for Earth and Titan Entry, Ph.D. Thesis, Virginia Polytechnic Institute and State University, Blacksburg, 2006Google Scholar
  14. 14.
    R.N. Gupta et al., A Review of Reaction Rates and Thermodynamic and Transport Properties for an 11-Species Air Model for Chemical and Thermal Nonequilibrium Calculations to 30000 K. NASA STI/Recon Technical Report N, 90, 27064 (1990)Google Scholar

Copyright information

© Springer International Publishing AG, part of Springer Nature 2019

Authors and Affiliations

  • Jun Ming Lyu
    • 1
  • X. L. Cheng
    • 1
  • J. J. Yu
    • 1
  • F. Li
    • 2
  • X. L. Yu
    • 2
  1. 1.China Academy of Aerospace AerodynamicsBeijingChina
  2. 2.Key Laboratory of High Temperature Gas DynamicsInstitute of Mechanics, Chinese Academy of SciencesBeijingChina

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