Comparisons of coupled radiative Navier-Stokes flow solutions with the Project Fire II flight data

Olynick, David R.; Henline, William D.; Chambers, L. H.; Candler, Graham V.; Rasky, Daniel J.

doi:10.2514/6.1994-1955

Cited by 29 publications

(35 citation statements)

References 5 publications

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“…The absorbed radiative flux refers to the component that is absorbed by the beryllium calorimeter over the entire spectrum. The spectral absorptance of beryllium is reported by 4,5,6,7,8,9,10,11,12,13 . Table 2 lists those studies published since 1984, which are the most relevant to modern studies.…”

Section: Review Of Past Studiesmentioning

confidence: 99%

Nonequilibrium Stagnation-Line Radiative Heating for Fire II

Johnston

Hollis

Sutton

2008

Journal of Spacecraft and Rockets

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This paper presents a detailed analysis of the shock-layer radiative heating to the Fire II vehicle using a new air radiation model and a viscous shock-layer flowfield model. This new air radiation model contains the most up-to-date properties for modeling the atomic-line, atomic photoionization, molecular band, and non-Boltzmann processes. The applied viscous shock-layer flowfield analysis contains the same thermophysical properties and nonequilibrium models as the LAURA Navier-Stokes code. Radiation-flowfield coupling, or radiation cooling, is accounted for in detail in this study. It is shown to reduce the radiative heating by about 30% for the peak radiative heating points, while reducing the convective heating only slightly. A detailed review of past Fire II radiative heating studies is presented. It is observed that the scatter in the radiation predicted by these past studies is mostly a result of the different flowfield chemistry models and the treatment of the electronic state populations. The present predictions provide, on average throughout the trajectory, a better comparison with Fire II flight data than any previous study. The magnitude of the vacuum ultraviolet (VUV) contribution to the radiative flux is estimated from the calorimeter measurements. This is achieved using the radiometer measurements and the predicted convective heating. The VUV radiation predicted by the present model agrees well with the VUV contribution inferred from the Fire II calorimeter measurement, although only when radiation-flowfield coupling is accounted for. This agreement provides evidence that the present model accurately models the VUV radiation, which is shown to contribute significantly to the Fire II radiative heating. ν / c VUV = vacuum ultraviolet; refers to the spectral region above 6 eV Nomenclature

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Section: Review Of Past Studiesmentioning

confidence: 99%

Nonequilibrium Stagnation-Line Radiative Heating for Fire II

Johnston

Hollis

Sutton

2008

Journal of Spacecraft and Rockets

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“…These assumptions constitute a minimum acceptable model (Ref. 17) for a CFD code even if the radiation solver is uncoupled. Four additional flow solvers considered and which satisfy these criteria are GASP, NEDANA, GPACT, and NSHYP.…”

Section: Codes Employedmentioning

confidence: 99%

“…Also, these radiation codes were coupled with the flow solvers LAURA (Ref. 17) and GIANTS ( Ref. 17), respectively.…”

Section: Codes Employedmentioning

confidence: 99%

Free-Piston Shock Tunnel Test Technique Development: An AEDC/DLR Cooperative Program

Stallings¹,

Williams²,

Felderman³

2003

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“…Two flight tests of the Apollo command modules were conducted at orbital (Apollo-09,11) and at super-orbital speeds (Apollo17,20) [13]. In the present the numerical investigation bases on some previously published works [14][15][16][17][18]. Detailed analysis of radiative gas dynamics of experimental space vehicles Fire-II and Stardust was presented in [14,15].…”

Section: Introductionmentioning

confidence: 99%

“…In the present the numerical investigation bases on some previously published works [14][15][16][17][18]. Detailed analysis of radiative gas dynamics of experimental space vehicles Fire-II and Stardust was presented in [14,15]. Several recent publications were dedicated to studying the real re-entry conditions of super-orbital capsule [16,17].…”

Section: Introductionmentioning

confidence: 99%

Spatial Multiphysics Models of the Radiation Gas Dynamics of Super Orbital Re-Entry Space Vehicles

Суржиков

2017

J. Phys.: Conf. Ser.

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Abstract. The multiphysics models of non equilibrium physical and chemical processes that should be considered together with radiative gas dynamic models for a description of the aero physics of super-orbital space vehicles are described.As an example of application of the multiphysics approach a three-dimensional numerical simulation analysis of radiative gas dynamics of Apollo-17 command module is analyzed. The results of calculations are compared with other numerical predictions, analytical correlations, and available experimental data.

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Comparisons of coupled radiative Navier-Stokes flow solutions with the Project Fire II flight data

Cited by 29 publications

References 5 publications

Nonequilibrium Stagnation-Line Radiative Heating for Fire II

Nonequilibrium Stagnation-Line Radiative Heating for Fire II

Free-Piston Shock Tunnel Test Technique Development: An AEDC/DLR Cooperative Program

Spatial Multiphysics Models of the Radiation Gas Dynamics of Super Orbital Re-Entry Space Vehicles

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