Study of Aero-thermal Effects with Heat Radiation in Optical Side Window
In hypersonic environments, the aerothermal effect
makes it difficult for the optical side windows of optical guided
missiles to withstand high heat. This produces cracking or breaking,
resulting in an inability to function. This study used computational
fluid mechanics to investigate the external cooling jet conditions of
optical side windows. The turbulent models k-ε and k-ω were
simulated. To be in better accord with actual aerothermal
environments, a thermal radiation model was added to examine
suitable amounts of external coolants and the optical window
problems of aero-thermodynamics. The simulation results indicate that
when there are no external cooling jets, because airflow on the optical
window and the tail groove produce vortices, the temperatures in these
two locations reach a peak of approximately 1600 K. When the
external cooling jets worked at 0.15 kg/s, the surface temperature of
the optical windows dropped to approximately 280 K. When adding
thermal radiation conditions, because heat flux dissipation was faster,
the surface temperature of the optical windows fell from 280 K to
approximately 260 K. The difference in influence of the different
turbulence models k-ε and k-ω on optical window surface temperature
was not significant.
[1] X. Y. Yang, C. H. Liu, and Y. Q. Gu,"Design of hypersonic vehicle
infrared cooling dome,"Infrared and Laser Engineeringe, vol. 33, no. 6,
pp. 576-579, Dec. 2004.
[2] C. C. Li, Y. C. Lin and, M. C. Hsieh, "3-D simulation of external cooling
of aero-optical side window," in 2011 FDTT. pp. 214-218.
[3] J. J. Bertin, and R. M. Cummings, " Fifty years of hypersonics: where
we-ve been, where we-re going," Progress in Aerospace Sciences, vol.39,
pp.511-536, 2003.
[4] K. H. Neale, and, B. M. L. "Active cooling from the sixties to NASP," In:
Current technology for thermal protection systems," NASA CP 3157,
1992.
[5] E. H. Hirschel, Basic of Aerodynamic,.Springer-Verlag, 2005.
[6] J. Bartl, and M. Baranek, " Emissivity of aluminium and its important for
radiometric measurement," Measurement of Physical Quantities, vol. 4,
pp.31-36, 2004.
[7] E. R. Dobrovinskaya, L. A. Lytvynov, and V. Pishchik,
Sapphire :Material, Manufacturing, Applications, Springer-Verlag, 2009,
pp.80-95.
[8] M. Algacyr. Jr., and C. Ndaona, "Hypersonic flow past open cavities,"
AIAA Journal, vol.32, issue.12, pp.2387-2393, 1994.
[1] X. Y. Yang, C. H. Liu, and Y. Q. Gu,"Design of hypersonic vehicle
infrared cooling dome,"Infrared and Laser Engineeringe, vol. 33, no. 6,
pp. 576-579, Dec. 2004.
[2] C. C. Li, Y. C. Lin and, M. C. Hsieh, "3-D simulation of external cooling
of aero-optical side window," in 2011 FDTT. pp. 214-218.
[3] J. J. Bertin, and R. M. Cummings, " Fifty years of hypersonics: where
we-ve been, where we-re going," Progress in Aerospace Sciences, vol.39,
pp.511-536, 2003.
[4] K. H. Neale, and, B. M. L. "Active cooling from the sixties to NASP," In:
Current technology for thermal protection systems," NASA CP 3157,
1992.
[5] E. H. Hirschel, Basic of Aerodynamic,.Springer-Verlag, 2005.
[6] J. Bartl, and M. Baranek, " Emissivity of aluminium and its important for
radiometric measurement," Measurement of Physical Quantities, vol. 4,
pp.31-36, 2004.
[7] E. R. Dobrovinskaya, L. A. Lytvynov, and V. Pishchik,
Sapphire :Material, Manufacturing, Applications, Springer-Verlag, 2009,
pp.80-95.
[8] M. Algacyr. Jr., and C. Ndaona, "Hypersonic flow past open cavities,"
AIAA Journal, vol.32, issue.12, pp.2387-2393, 1994.
@article{"International Journal of Mechanical, Industrial and Aerospace Sciences:58099", author = "Chun-Chi Li and Da-Wei Huang and Yin-Chia Su and Liang-Chih Tasi", title = "Study of Aero-thermal Effects with Heat Radiation in Optical Side Window", abstract = "In hypersonic environments, the aerothermal effect
makes it difficult for the optical side windows of optical guided
missiles to withstand high heat. This produces cracking or breaking,
resulting in an inability to function. This study used computational
fluid mechanics to investigate the external cooling jet conditions of
optical side windows. The turbulent models k-ε and k-ω were
simulated. To be in better accord with actual aerothermal
environments, a thermal radiation model was added to examine
suitable amounts of external coolants and the optical window
problems of aero-thermodynamics. The simulation results indicate that
when there are no external cooling jets, because airflow on the optical
window and the tail groove produce vortices, the temperatures in these
two locations reach a peak of approximately 1600 K. When the
external cooling jets worked at 0.15 kg/s, the surface temperature of
the optical windows dropped to approximately 280 K. When adding
thermal radiation conditions, because heat flux dissipation was faster,
the surface temperature of the optical windows fell from 280 K to
approximately 260 K. The difference in influence of the different
turbulence models k-ε and k-ω on optical window surface temperature
was not significant.", keywords = "aero-optical side window, aerothermal effect, cooling,
hypersonic flow", volume = "6", number = "5", pages = "933-5", }