Research Article  Open Access
Romain Savajano, Daniel F. Potter, Ojas Joshi, Pénélope Leyland, "Radiation Analysis for Two Trajectory Points of the Fire II Entry", International Journal of Aerospace Engineering, vol. 2012, Article ID 597930, 9 pages, 2012. https://doi.org/10.1155/2012/597930
Radiation Analysis for Two Trajectory Points of the Fire II Entry
Abstract
Numerical rebuilding of two trajectory points ( s and s) of the Fire II mission has been carried out to predict the radiative heat flux for nonequilibrium and closetoequilibrium conditions. The simulations have been performed with eilmer3 in an uncoupled way and using a tangent slab method for the radiation transport. Different population models (QSS and Boltzmann) have been compared, and the influence of catalytic wall condition was taken into account. An analysis on the spectral range and on the spectral resolution has also been carried out.
1. Introduction
During atmospheric (re)entries, planetary probes encounter high heat fluxes due to their significant speed (up to 11 km/s for an Earth reentry). Such excessive thermal loads can damage the onboard equipment and compromise the safety of the passengers in case of a mannedflight mission. As a consequence, the sizing of the thermal protection system (TPS) is a crucial step in the preliminary design study of a probe.
The Fire II mission took place in May 22nd, 1965 [1]. Its main goal was the assessment of the radiative heating environment during an Earth reentry. The vehicle geometry was an Apollo type with a reentry velocity of 11.4 km/s. The fore body consisted in a three layer configuration formed by phenolicasbestos heatshield sandwiched between beryllium calorimeters. The contribution from the radiation of the hot plasma to the total heat flux received by the probe was up to 40%. This paper concentrates on this radiative contribution. The reconstruction of radiation spectra for the Fire II experiment has been already discussed in numerous papers [2–4].
Two points of the trajectory of the Fire II mission have been numerically rebuilt. The first one at s corresponds to nonequilibrium conditions whereas the second one at s is close to equilibrium conditions, even if a small region behind the shock is nonequilibrium. Figure 1 gives the temperature profiles of the translationalrotational temperature and the vibrationalelectronic temperature for the two simulations.
In this work, the code retained for the simulations is eilmer3, a multiblock compressible NavierStokes solver described in Section 2. Section 3 is dedicated to the results of the simulations.
An analysis of the spectral range has been performed to assess the wavelength range of interest and the number of points needed for a good accuracy. Then two different population models (QSS and Boltzmann) have been compared and the influence of the catalytic wall condition discussed. Finally, a comparison with the flight data taken by the calorimeters was made.
2. Description of Flow Field Solver
In this work, the eilmer3 [5, 6] multiblock compressible NavierStokes solver was used to generate the CFD solutions. The implementation of the governing equations, diffusion model, and radiation transport models in eilmer3 are presented in Section 2.1. Eilmer3 makes use of external gas property and thermochemical nonequilibrium modules, which are described in Section 2.2 and 2.3.
2.1. Axisymmetric NavierStokes Solver: Eilmer3
The eilmer3 code is a multiple blockstructured finite volume code. It is capable of considering planar, axisymmetric, and fully threedimensional geometries; only the axisymmetric formulations are considered here.
2.1.1. Implementation of the Governing Equations
The code solves the compressible NavierStokes equations via a cellcentred timedependent finitevolume formulation:
In the present work, a twotemperature formulation of the NavierStokes equations is implemented. The inviscid gasdynamics, viscous effects, finiterate chemistry, and thermal energy exchange are treated with an operatorsplit approach, where the respective flux vectors and source terms are applied in a loosely coupled manner. The vector of conserved quantities therefore consists of total mass, total momentum, total energy, vibrationelectronelectronic energy, and species mass: where is density, is velocity, is total energy, is the vibrationelectronelectronic energy, and is the species massfraction. Both total and species masses are considered in order to implement the massconserved formulation of the chemical kinetic ODE system proposed by Gollan [7]. In contrast, translationrotation energy is not considered as a conserved quantity as it can be calculated from the definition of total energy. The inviscid flux vector components are where is the electron pressure, and the viscous component is where denotes the axisymmetric viscous stress components, is heat flux, and is diffusion flux. The vector of source terms is separated into geometric, chemical kinetic, thermal energy exchange, and radiation contributions in order to apply the operatorsplitting integration approach: where
Here is the cell area, is the species mole weight, is the radiative source term (included in both total and vibrationelectronicelectron energies), and , , , and are the source terms for vibrationchemistry coupling, electronchemistry coupling, vibrationtranslation exchange, and electrontranslation exchange, respectively.
2.1.2. Integration, Flux Calculators, and Boundary Conditions
The inviscid and viscous flux vectors are integrated via a predictorcorrector method, the chemical source terms via an QSS method, and the energy source terms via a fourth order RungeKutta method. The radiative source terms are fully coupled with the inviscid update but are not reevaluated for the corrector step. The inviscid fluxes are computed via a dissipative equilibrium flux method [8] in the vicinity of shocks and the AUSMDV [9] scheme elsewhere. Boundary conditions are applied via two layers of ghost cells surrounding the computational domain.
2.1.3. Diffusion
The effective diffusion coefficients for all neutral species are calculated in a simple manner by assuming a constant Lewis number: where is the Prandtl number and for reacting air. For ions, the ambipolar correction proposed by Gnoffo et al. [10] is implemented to maintain charge neutrality. The diffusive mass flux of species is then calculated according to the approximate form of Fick’s first law:
2.2. HighTemperature Gas Property Module
2.2.1. Thermodynamic Coefficients
The thermodynamic coefficients for partially ionised gases in the ArCNO elemental system are calculated based on the assumption of fully decoupled internal thermal modes. For the air testgas in the present work, the 11 species considered are N_{2}, , , , , , , , , , and . Negative ions are not considered based on their low concentrations. Translation and rotation are modelled under the assumption of full excitation. Molecular vibration is described by the truncated harmonic oscillator model. The thermodynamic contributions of the electronic thermal modes are calculated by direct summation over the electronic levels, truncated at specific levels that maximise the efficiency and accuracy of the calculation. Comparisons with the CEA2 code [11] demonstrate good agreement for molecules up to temperatures of 5,000 K and good agreement for atoms up to temperatures of 11,000 K. The errors found above these temperatures ranges are due to the assumption of fully decoupled thermal modes and are unavoidable for the generalised multitemperature context the module was designed for.
2.2.2. Transport Coefficients
The thermal nonequilibrium transport coefficients are calculated via the multicomponent mixture rules proposed by Gupta et al. [12]. The collision integrals recommended by Wright and Levin [13] and Wright et al. [14, 15] are preferred over those given in [12] as the former are based on recent computational chemistry calculations where available. Good agreement is found with the CEA2 code [11] for the viscosity of equilibrium air in the temperature range K.
2.2.3. Spectral Radiation Coefficients
The spectral radiation coefficients are calculated by an inhouse linebyline model for atomic and diatomic boundbound transitions, and curvefits and hydrogenic approximations for continuum transitions. Electronic level and atomic line data were obtained from NIST [16], and the diatomic electronic transition moments presented by Chauveau et al. [17] and Babou et al. [18] are implemented. Following the recommendations of Johnston [19], atomic lines are modelled individually for eV and as multiplets for eV. For diatomic radiators, transitions are modelled via Hund’s case (b), transitions are modelled via the intermediate (a)(b) case, and the remaining transitions are modelled via Hund’s case (a). Continuum transitions were modelled by the step model of Johnston [19] for N and O photoionisation and with hydrogenic approximations otherwise. The model implementation has been verified by comparisons with the SPRADIAN07 code [20].
Electronic level populations for N_{2}, N_{2} ^{+}, N, and O are calculated by a collisionalradiative model applied in the QSS limit. The other radiators considered in this work (N^{+} and O^{+}) are assumed to be populated by Boltzmann distributions. For N_{2} and N_{2} ^{+}, the rate coefficient models compiled by Johnston [19] are implemented. For N and O, the mechanisms considered are (1) electron impact excitation, (2) electron impact ionisation, and (3) boundbound radiative transitions. The models implemented for each, in order of preference, are summarised in Table 1. Experiment or computational chemistry based rate coefficients are preferred for low lying levels, while simple hydrogenic models are implemented for the remainder.

2.3. Thermochemical Nonequilibrium Module
2.3.1. Chemical Kinetics
The chemical kinetics of bulk species are considered by both flow solvers (as opposed to electronically or vibrationally specific models). The ratecontrolling temperature approach for modelling reactions in thermal nonequilibrium is adopted; the ratecontrolling temperatures for the various classes of reactions considered are summarised in Table 2. Following the recommendations of Lino da Silva et al. [26], the vibrational temperature exponent is set to 0.7 for compression flows and 0.5 for expansion flows. The forward rates from the 11 species air reaction scheme proposed by Park [27] are implemented; however, the radiative recombination reactions are omitted. The backward rates for these reactions are calculated as where the equilibrium constant is calculated via the Gibbs free energy approach.

2.3.2. Thermal Energy Exchange
Vibrationtranslation exchange is modelled via the LandauTeller equation. The relaxation times are calculated by the Millikan and White [28] expressions with the hightemperature correction proposed by Park [27]. The heating of electrons through elastic collisions with heavy particles is modelled by the rate equation derived by Appleton and Bray [29]. For Coulomb collisions between electrons and ions, the effective collision frequency is derived from [29], and the effective collision frequency for electronneutral interactions is calculated via the curve fits given by Gnoffo et al. [10].
3. Fire II Simulations
3.1. Flow Conditions
In this work two trajectory points of the Fire II flight experiment are considered: s and s. Consequently, a nonequilibrium case and a closetoequilibrium case can be considered. Table 3 gives the flow conditions for these two trajectory points [1].

For all the simulations, a twotemperature model was assumed: T_{tr,rot} and T_{vib,el}. Simulations have been performed with both noncatalytic and super catalytic wall conditions (recombination to the inflow conditions). The influence of this boundary condition on the radiative heat flux is discussed in Section 3.3.4.
3.2. Grid Convergence
The simulation strategy is the same for the two trajectory points. Start the simulations on a coarse grid without any viscous effects and chemical reactions. After one body length, the chemical reactions are started, then after another body length the viscous effects are progressively taken into account. Several body lengths are then necessary to ensure the good convergence of the simulations. Three different meshes were used in order to reach a converged solution: , , and . Figure 2 shows the convergence of the radiative heat flux at the stagnation point, and Figure 3 gives the density residuals evolution for the two trajectory points. The final mesh retained for analysis in both cases was a grid refined at the wall.
(a) 1634s
(b) 1643s
3.3. Radiation Analysis
For the two trajectory points, the radiative heat flux at the stagnation point has been evaluated through uncoupled simulations with a tangent slab method [30] (100 cells per row are considered) for the radiation transport.
The divergence for a cell is given by
As discussed in Section 2, the only species considered for radiation are N_{2}, N_{2} ^{+}, N, N^{+}, O, and O^{+}. NO was not included as a radiating species as its concentration was almost null. Figure 4 shows the species mass fractions on the stagnation line for the two trajectory points. It can be noticed that 95% of the flow after the shock is composed of N, O, and N^{+}.
(a) 1634
(b) 1643
3.3.1. Spectral Range Analysis
First, simulations were performed to assess the wavelength range necessary for the study. The range 50 to 4000 nm was considered with a spectral resolution of 100 points per nm. The results obtained are displayed in Figure 5.
(a) 1634
(b) 1643
In both cases, it can be noticed that 98% of the contribution is coming from wavelengths between 50 and 2000 nm. For further analysis, the spectral range of study can then be reduced to 50 to 2000 nm.
3.3.2. Spectral Resolution Analysis
For the two trajectory points, a study has been performed on the influence of the spectral resolution. Simulations with 10, 100, and 1000 points per nm have been done. The results are plotted in Figure 6.
(a) 1634
(b) 1643
In both cases, the conclusion can be made that 100 points per nm are sufficient for computing the radiative heat flux.
3.3.3. Boltzmann versus QSS
After the discussions on spectral ranges and resolutions, two population models have been compared: Boltzmann and QSS approximation. Figure 7 give the results obtained.
(a) 1634
(b) 1643
As expected, for the low density case (), which is completely at nonequilibrium, simulations with Boltzmann model are clearly overestimating the radiative heat flux, whereas at the higher density case, close to thermal equilibrium, the two models are giving almost the same results.
3.3.4. Super Catalytic Wall versus Noncatalytic Wall
The Fire II onboard equipment was protected by heat shields containing beryllium which is highly catalytic to reactions. Consequently, the first assumptions were to consider the wall as fully catalytic [4]. However as explained by Olynick et al. [3], due to the presence of oxygen in the flow, the beryllium is likely to be oxidised and thus having less catalytic effects. For the two trajectory points, simulations were performed with and without the catalytic wall condition. Figure 8 shows the radiative intensity obtained in both cases.
(a) 1634
(b) 1643
For the two trajectory points, the catalytic wall condition leads to a lower heat flux but the two values are still pretty close.
3.3.5. Comparison with Flight Data
The results obtained for the stagnation point can be compared with flight data [1] using the data measured by the calorimeter and the radiometer. The calorimeter has measured the total heating rate minus the radiative flux absorpted by the beryllium shield, that is, , where is the absorptance of the beryllium heat shield. The radiometer value gives directly the value for the radiative heat flux. However, the VUV contribution is not taken into account in this measure. In Figure 9, a comparison is given with values obtained from the simulations in this work. It can be noticed that there is a discrepancy between the values from the calorimeter and the values obtained here when using the authors convective heat flux value. However, when using an average value for the convective heat flux (independently of the catalytic wall condition) coming from previous works [2–4, 31], the agreement is much more better. It is explained by the fact that the diffusive heat flux is not taken into account correctly in the evaluation of the convective heat flux in our simulations. For the comparison with the radiometer, the trajectory point at 1634s is in good agreement (regarding the fact that a major contribution from VUV has been calculated). However, for the 1643s trajectory point, the radiative heat flux calculated seems to be too low in comparison with the flight data.
4. Conclusions
In this work, the uncoupled radiative heat flux for two trajectory points of the Fire II experiment has been rebuilt with a tangent slab model. It was first shown that the entire radiative heat flux was coming from the wavelength range 50 to 2000 nm and that 100 points per nm were sufficient to get a good accuracy with a tangent slab approach. It has also been confirmed that for s, the flow is close to the thermal equilibrium as the two different population models (Boltzmann and QSS) are leading to the same results, whereas at s, there is a strong discrepancy between the two methods. As for the catalytic wall condition, its influence on the radiative heat flux is negligible for the two trajectory points. The results obtained for the radiative heat flux are in good agreement with flight data.
Acknowledgment
This work was partially supported by the ESANPI Program, CCN C21872.
References
 D. L. Cauchon, “Radiative heating results from the FIRE II flight experiment at a reentry velocity of 11. km/s,” Tech. Rep. TM X1402, NASA, 1967. View at: Google Scholar
 C. O. Johnston and B. R. Hollis, “Nonequilibrium stagnationline radiative heating for Fire II,” Journal of Spacecraft and Rockets, vol. 45, no. 6, pp. 1185–1195, 2008. View at: Publisher Site  Google Scholar
 D. R. Olynick, W. D. Henline, L. H. Chambers, and G. V. Candler, “Comparison of coupled radiative flow solutions with project fire II flight data,” Journal of Thermophysics and Heat Transfer, vol. 9, no. 4, pp. 586–594, 1995. View at: Google Scholar
 R. B. Greendyke and L. C. Hartung, “Convective and radiative heat transfer analysis for the fire II forebody,” Journal of Spacecraft and Rockets, vol. 31, no. 6, pp. 986–992, 1994. View at: Google Scholar
 P. A. Jacobs, “MB CNS: a computer program for the simulation of transient compressible flows; 1998 update,” Tech. Rep. 7/98, Department of Mechanical Engineering, The University of Queensland, Brisbane, Australia, 1998. View at: Google Scholar
 D. Potter, S. Karl, and P. Leyland, “TN032—EPFL Contribution to ESATRP AMOD,” Tech. Rep., ESA, 2009. View at: Google Scholar
 R. J. Gollan, Computational modelling of hightemperature gas effects with application to hypersonic flows, Ph.D. thesis, School of Engineering, The University of Queensland, June 2008.
 M. N. Macrossan, “The equilibrium flux method for the calculation of flows with nonequilibrium chemical reactions,” Journal of Computational Physics, vol. 80, no. 1, pp. 204–231, 1989. View at: Google Scholar
 Y. Wada and M. S. Liou, “A flux splitting scheme with highresolution and robustness for discontinuities,” Tech. Rep. 940083, AIAA, January 1994. View at: Google Scholar
 P. A. Gnoffo, R. N. Gupta, J. L. Shinn, and United States, “Conservation equations andphysical models for hypersonic air flows in thermal and chemical equilibrium,” Tech. Rep. TP2867, NASA, 1989, Book, microform. View at: Google Scholar
 B. J. McBride and S. Gordon, “Computer program for calculation of complex chemical equilibrium compositions and applications, part 2: users manual and program description,” Tech. Rep. 1311, NASA, 1996. View at: Google Scholar
 R. N. Gupta, J. M. Yos, R. A. Thompson, and K. Lee, “A review of reaction rates and thermodynamicand transport properties for an 11species air model for chemical and thermal nonequilibrium calculations to 30000 K,” Tech. Rep., NASA STI/Recon, August 1990. View at: Google Scholar
 M. J. Wright and E. Levin, “Collision integrals for ionneutral interactions of air and argon,” Journal of Thermophysics and Heat Transfer, vol. 19, no. 1, pp. 127–128, 2005. View at: Google Scholar
 M. J. Wright, D. Bose, G. E. Palmer, and E. Levin, “Recommended collision integrals for transport property computations, part 1: air species,” AIAA Journal, vol. 43, no. 12, pp. 2558–2564, 2005. View at: Publisher Site  Google Scholar
 M. J. Wright, H. H. Hwang, and D. W. Schwenke, “Recommended collision integrals for transport property computations part 2: mars and venus entries,” AIAA Journal, vol. 45, no. 1, pp. 281–288, 2007. View at: Publisher Site  Google Scholar
 NIST Chemical Kinetics Database, Ver. 7.0, 2003.
 S. Chauveau, M. Y. Perrin, P. Rivière, and A. Soufiani, “Contributions of diatomic molecular electronic systems to heated air radiation,” Journal of Quantitative Spectroscopy and Radiative Transfer, vol. 72, no. 4, pp. 503–530, 2002. View at: Publisher Site  Google Scholar
 Y. Babou, P. Riviere, M. Y. Perrin, and A. Soufiani, “Hightemperature and non equilibrium partition function and thermodynamic data of diatomic molecules,” International Journal of Thermophysics, vol. 30, pp. 416–438, 2009. View at: Google Scholar
 C. Johnston, Nonequilibrium shocklayer radiative heating for Earth and Titan entry, Ph.D. thesis, Virginia Polytechnic Institute and State University, Blacksburg, Va, USA, 2006.
 S.Y. Hyun, Radiation code SPRADIAN07 and its applications, Ph.D. thesis, School of Mechanical, Aerospace and Systems Engineering, Division of Aerospace Engineering, KAIST, Daejeon, Korea, 2009.
 R. M. Frost, P. Awakowicz, H. P. Summers, and N. R. Badnell, “Calculated cross sections and measured rate coefficients for electronimpact excitation of neutral and singly ionized nitrogen,” Journal of Applied Physics, vol. 84, no. 6, pp. 2989–3003, 1998. View at: Google Scholar
 M. Gryziński, “Classical theory of electronic and ionic inelastic collisions,” Physical Review, vol. 115, no. 2, pp. 374–383, 1959. View at: Publisher Site  Google Scholar
 W. H. Soon and J. A. Kunc, “Thermal nonequilibrium in partially ionized atomic oxygen,” Physical Review A, vol. 41, no. 2, pp. 825–843, 1990. View at: Publisher Site  Google Scholar
 M. Panesi, Physical models for nonequilibrium plasma flow simulations at high speed reentry conditions, Ph.D. thesis, von Karman Institute for Fluid Dynamics, RhodeSaintGenèse, Belgium, 2009.
 O. Zatsarinny and S. S. Tayal, “Electron collisional excitation rates for O I using the Bspline Rmatrix approach,” Astrophysical Journal, Supplement Series, vol. 148, no. 2, pp. 575–582, 2003. View at: Publisher Site  Google Scholar
 M. Lino da Silva, V. Guerra, and J. Loureiro, “Twotemperature models for nitrogen dissociation,” Chemical Physics, vol. 342, no. 1–3, pp. 275–287, 2007. View at: Publisher Site  Google Scholar
 C. Park, “Review of chemicalkinetic problems of future NASA missions, I: earth entries,” Journal of Thermophysics and Heat Transfer, vol. 7, no. 3, pp. 385–398, 1993. View at: Google Scholar
 R. C. Millikan and D. R. White, “Systematics of vibrational relaxation,” The Journal of Chemical Physics, vol. 39, no. 12, pp. 3209–3213, 1963. View at: Google Scholar
 J. P. Appleton and K. N. C. Bray, “The conservation equations for a nonequilibrium plasma,” Journal of Fluid Mechanics, vol. 20, no. 4, pp. 659–672, 1964. View at: Google Scholar
 M. F. Modest, Radiative Heat Transfer, Academic Press, London, UK, 2nd edition, 2003.
 G. E. Palmer, T. White, and A. Pace, “Direct coupling of the NEQAIR radiation and DPLR computational fluid dynamic codes,” Journal of Spacecraft and Rockets, vol. 48, pp. 836–845, 2011. View at: Google Scholar
Copyright
Copyright © 2012 Romain Savajano et al. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.