Stagnation-point heat transfer rates for Pioneer-Venus probes

Park, Chul; Ahn, Hyo-Keun

doi:10.2514/6.1998-832

Cited by 14 publications

(23 citation statements)

References 17 publications

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“…In Fig. 10, the radiative heat flux values calculated for the Pioneer-Venus vehicle which entered into Venus are shown [21]. As seen here, the heat flux values are indeed quite high.…”

Section: Radiation In Other Planetsmentioning

confidence: 64%

Radiation Phenomena in Planetary Entries

Park¹

2013

International Journal of Aeronautical and Space Sciences

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Radiative heating phenomena occurring in planetary entry flights are reviewed for the purpose of educating those who are not familiar with the problem. How the radiative heat transfer rates to the Apollo entry vehicle were measured and analyzed are first described. Next, the effects of thermo-chemical non-equilibrium on radiation are summarized. Then the radiation problems in entry flights into other planets are reviewed. Finally, unsolved problems are enumerated.

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“…In Fig. 10, the radiative heat flux values calculated for the Pioneer-Venus vehicle which entered into Venus are shown [21]. As seen here, the heat flux values are indeed quite high.…”

Section: Radiation In Other Planetsmentioning

confidence: 64%

Radiation Phenomena in Planetary Entries

Park¹

2013

International Journal of Aeronautical and Space Sciences

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“…The first set was developed by Park 6 and the second set was developed by Zhluktov. 7 In this study, the nitridation reaction in the original Park's model is replaced by the nitrogen recombination reaction to be consistent with observations in arc-jet tests using pure nitrogen gas.…”

Section: Chemistry Modelsmentioning

confidence: 99%

“…Two sets of non-equilibrium gas/surface interaction chemistry between air and carbon surface are studied. They were developed by Park 6 and Zhluktov, 7 respectively. Coupled fluid-material response analyses of stagnation tests conducted in NASA Ames Research Center arc-jet facilities are performed.…”

Section: Introductionmentioning

confidence: 99%

Effect of Nonequilibrium Surface Thermochemistry in Simulation of Carbon-Based Ablators

Chen

Gökçen

2013

Journal of Spacecraft and Rockets

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This study demonstrates that coupling of a material thermal response code and a flow solver using non-equilibrium gas/surface interaction model provides time-accurate solutions for the multidimensional ablation of carbon based charring ablators. The material thermal response code used in this study is the Two-dimensional Implicit Thermal-response and AblatioN Program (TITAN), which predicts charring material thermal response and shape change on hypersonic space vehicles. Its governing equations include total energy balance, pyrolysis gas mass conservation, and a three-component decomposition model. The flow code solves the reacting Navier-Stokes equations using Data Parallel Line Relaxation (DPLR) method. Loose coupling between the material response and flow codes is performed by solving the surface mass balance in DPLR and the surface energy balance in TITAN. Thus, the material surface recession is predicted by finite-rate gas/surface interaction boundary conditions implemented in DPLR, and the surface temperature and pyrolysis gas injection rate are computed in TITAN. Two sets of nonequilibrium gas/surface interaction chemistry between air and the carbon surface developed by Park and Zhluktov, respectively, are studied.

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“…The first set was developed by Park 6 and the second set was developed by Zhluktov. 7 In this study, the nitridation reaction in the original Park's model is replaced by the nitrogen recombination reaction to be consistent with the observation in the arc-jet tests using pure nitrogen gas.…”

Section: Chemistry Modelsmentioning

confidence: 99%

“…Two sets of finite-rate gas/surface interaction chemistry between air and carbon surface are studied. They were developed by Park 6 and Zhluktov, 7 respectively. Coupled fluid-material response analyses of stagnation tests conducted in NASA Ames Research Center arc-jet facilities are performed.…”

Section: Introductionmentioning

confidence: 99%

Effect of Surface Nonequilibrium Thermochemistry in Simulation of Carbon Based Ablators

Chen

Gökçen

2012

43rd AIAA Thermophysics Conference

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This study demonstrates that coupling of a material thermal response code and a flow solver using finite-rate gas/surface interaction model provides time-accurate solutions for multidimensional ablation of carbon based charring ablators. The material thermal response code used in this study is the Twodimensional Implicit Thermal Response and Ablation Program (TITAN), which predicts charring material thermal response and shape change on hypersonic space vehicles. Its governing equations include total energy balance, pyrolysis gas momentum conservation, and a three-component decomposition model. The flow code solves the reacting Navier-Stokes equations using Data Parallel Line Relaxation (DPLR) method. Loose coupling between material response and flow codes is performed by solving the surface mass balance in DPLR and the surface energy balance in TITAN. Thus, the material surface recession is predicted by finite-rate gas/surface interaction boundary conditions implemented in DPLR, and the surface temperature and pyrolysis gas injection rate are computed in TITAN. Two sets of gas/surface interaction chemistry between air and carbon surface developed by Park and Zhluktov, respectively, are studied. Coupled fluid-material response analyses of stagnation tests conducted in NASA Ames Research Center arc-jet facilities are considered. The ablating material used in these arc-jet tests was a Phenolic Impregnated Carbon Ablator (PICA). Computational predictions of in-depth material thermal response and surface recession are compared with the experimental measurements for stagnation cold wall heat flux ranging from 107 to 1100 W/cm 2 . Nomenclature

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Stagnation-point heat transfer rates for Pioneer-Venus probes

Cited by 14 publications

References 17 publications

Radiation Phenomena in Planetary Entries

Radiation Phenomena in Planetary Entries

Effect of Nonequilibrium Surface Thermochemistry in Simulation of Carbon-Based Ablators

Effect of Surface Nonequilibrium Thermochemistry in Simulation of Carbon Based Ablators

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