Numerical Study of the Temperature History of Thermally Protected Blunt Nose during Flight

Amir Mahdi Tahsini; Seyed Amir Hosseini

doi:10.4028/www.scientific.net/AMM.598.294

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HomeApplied Mechanics and MaterialsApplied Mechanics and Materials Vol. 598Numerical Study of the Temperature History of...

Numerical Study of the Temperature History of Thermally Protected Blunt Nose during Flight

Abstract:

In the present work, the surface temperature history of a metal shell of the blunt nose of supersonic launch vehicle which is covered by a thermal protection coating is numerically predicted and compared with experimental data. The full Navier-Stokes equations are used to estimate the aerodynamic heat flux during flight, coupled with the governing equations for the thermal protection system to study the erosion rate and temperature variations. The results show the importance of the properties of the coating on accuracy of the numerical predictions.

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Periodical:

Applied Mechanics and Materials (Volume 598)

Pages:

294-297

DOI:

https://doi.org/10.4028/www.scientific.net/AMM.598.294

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Online since:

July 2014

Authors:

Amir Mahdi Tahsini*, Seyed Amir Hosseini

Keywords:

Aerodynamic Heating, Blunt Nose, Heat Conduction, Launch Vehicle, Numerical Simulation, Supersonic Flight, Thermal Protection System

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References

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