Approach to solution of coupled heat transfer problem on the surface of hypersonic vehicle of arbitrary shape

Bocharov, A. N.; Bityurin, V. A.; Golovin, N. N.; Евстигнеев, Н. М.; Petrovskiy, V P; Ryabkov, O. I.; Teplyakov, I. O.; Shustov, A. A.; Solomonov, Yu. S.; Фортов, В. Е.

doi:10.1088/1742-6596/774/1/012157

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“…Then, we solve the unsteady 3D Reynolds Averaged Navier Stokes equation coupled with 3D heat equation for the experimental test duration, with time steps being 1 μs. 31 The solution is obtained via iterative technique, wherein internal iterations with exchange of surface heat flux and temperature occur. Numerical iterations are continued till absolute convergence is achieved with residuals in the range of 1e −4 for mass, momentum (x, y, z-velocity), energy and turbulent viscosity.…”

Section: T a B L E 1 Flow Parameters In Shockmentioning

confidence: 99%

Shock wave‐material interaction in ZrB₂–SiC based ultra high temperature ceramics for hypersonic applications

2019

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We investigate the thermochemical stability of ZrB2–SiC based multiphase ceramics to hypersonic aerothermodynamic conditions in free piston shock tube with an objective to understand quantitatively the role of thermal shock and pressure. The developed ceramics sustained impulsive thermomechanical shock, under reflected shock pressure of 6.5 MPa and reflected shock temperature of 4160 K in dissociated oxygen, without structural failure. The conjugate heat transfer analysis predicts the surface temperature of ZrB2–SiC to reach a maximum of 693 and 865 K, for ZrB2–SiC–Ti. The transient shock‐material response is characterized by surface oxidation of the investigated ceramics, when exposed to high enthalpy gaseous environment, as a consequence of the interaction with ultrafast‐heated (106 K/s) gas for ~5 ms. Spectroscopic and structural characterization reveals that addition of Ti improves thermomechanical shock resistance, which is attributed to the assemblage of refractory phases. Taken together, ZrB2–SiC–Ti based multiphase ceramics exhibit favorable shock‐material response under impulse loading.

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Section: T a B L E 1 Flow Parameters In Shockmentioning

confidence: 99%

Shock wave‐material interaction in ZrB₂–SiC based ultra high temperature ceramics for hypersonic applications

2019

View full text Add to dashboard Cite

show abstract

Approach to solution of coupled heat transfer problem on the surface of hypersonic vehicle of arbitrary shape

Cited by 1 publication

References 3 publications

Shock wave‐material interaction in ZrB₂–SiC based ultra high temperature ceramics for hypersonic applications

Shock wave‐material interaction in ZrB₂–SiC based ultra high temperature ceramics for hypersonic applications

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Approach to solution of coupled heat transfer problem on the surface of hypersonic vehicle of arbitrary shape

Cited by 1 publication

References 3 publications

Shock wave‐material interaction in ZrB2–SiC based ultra high temperature ceramics for hypersonic applications

Shock wave‐material interaction in ZrB2–SiC based ultra high temperature ceramics for hypersonic applications

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Shock wave‐material interaction in ZrB₂–SiC based ultra high temperature ceramics for hypersonic applications

Shock wave‐material interaction in ZrB₂–SiC based ultra high temperature ceramics for hypersonic applications