Numerical study of thermochemical nonequilibrium flow around reentry capsule and estimation of aerodynamic heating

Y. Matsuda; H. Kihara; K. Abe

doi:10.1016/j.proeng.2013.12.025

Numerical study of thermochemical nonequilibrium flow around reentry capsule and estimation of aerodynamic heating

Y. Matsuda, H. Kihara, K. Abe

Thermophysics and Fluid Mechanics

Research output: Contribution to journal › Conference article › peer-review

Abstract

Numerical simulation of the flow fields was performed for the mission of Apollo AS-202 to investigate the influence of the laminar-turbulent transition position in the boundary layer around a reentry capsule on the heat flux at the wall. For this purpose, we intentionally varied the laminar-turbulent transition position and the obtained results were compared. According to the simulation result, in the turbulent case, heat flux value is about 1.4 times at maximum compared with the laminar case. It turned out that the transition position had a large influence on the heat flux at the wall, particularly in the forebody region. On the other hand, in the afterbody region, some discrepancies were seen compared with the flight data.

Original language	English
Pages (from-to)	261-269
Number of pages	9
Journal	Procedia Engineering
Volume	67
DOIs	https://doi.org/10.1016/j.proeng.2013.12.025
Publication status	Published - 2013
Event	7th Asian-Pacific Conference on Aerospace Technology and Science, APCATS 2013 - Sun-moon Lake, Taiwan, Province of China Duration: May 23 2013 → May 26 2013

All Science Journal Classification (ASJC) codes

Engineering(all)

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10.1016/j.proeng.2013.12.025

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title = "Numerical study of thermochemical nonequilibrium flow around reentry capsule and estimation of aerodynamic heating",

abstract = "Numerical simulation of the flow fields was performed for the mission of Apollo AS-202 to investigate the influence of the laminar-turbulent transition position in the boundary layer around a reentry capsule on the heat flux at the wall. For this purpose, we intentionally varied the laminar-turbulent transition position and the obtained results were compared. According to the simulation result, in the turbulent case, heat flux value is about 1.4 times at maximum compared with the laminar case. It turned out that the transition position had a large influence on the heat flux at the wall, particularly in the forebody region. On the other hand, in the afterbody region, some discrepancies were seen compared with the flight data.",

author = "Y. Matsuda and H. Kihara and K. Abe",

year = "2013",

doi = "10.1016/j.proeng.2013.12.025",

language = "English",

volume = "67",

pages = "261--269",

journal = "Procedia Engineering",

issn = "1877-7058",

publisher = "Elsevier BV",

note = "7th Asian-Pacific Conference on Aerospace Technology and Science, APCATS 2013 ; Conference date: 23-05-2013 Through 26-05-2013",

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T1 - Numerical study of thermochemical nonequilibrium flow around reentry capsule and estimation of aerodynamic heating

AU - Matsuda, Y.

AU - Kihara, H.

AU - Abe, K.

PY - 2013

Y1 - 2013

N2 - Numerical simulation of the flow fields was performed for the mission of Apollo AS-202 to investigate the influence of the laminar-turbulent transition position in the boundary layer around a reentry capsule on the heat flux at the wall. For this purpose, we intentionally varied the laminar-turbulent transition position and the obtained results were compared. According to the simulation result, in the turbulent case, heat flux value is about 1.4 times at maximum compared with the laminar case. It turned out that the transition position had a large influence on the heat flux at the wall, particularly in the forebody region. On the other hand, in the afterbody region, some discrepancies were seen compared with the flight data.

AB - Numerical simulation of the flow fields was performed for the mission of Apollo AS-202 to investigate the influence of the laminar-turbulent transition position in the boundary layer around a reentry capsule on the heat flux at the wall. For this purpose, we intentionally varied the laminar-turbulent transition position and the obtained results were compared. According to the simulation result, in the turbulent case, heat flux value is about 1.4 times at maximum compared with the laminar case. It turned out that the transition position had a large influence on the heat flux at the wall, particularly in the forebody region. On the other hand, in the afterbody region, some discrepancies were seen compared with the flight data.

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DO - 10.1016/j.proeng.2013.12.025

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SN - 1877-7058

VL - 67

SP - 261

EP - 269

JO - Procedia Engineering

JF - Procedia Engineering

T2 - 7th Asian-Pacific Conference on Aerospace Technology and Science, APCATS 2013

Y2 - 23 May 2013 through 26 May 2013

ER -

Numerical study of thermochemical nonequilibrium flow around reentry capsule and estimation of aerodynamic heating

Abstract

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