Abstract
Scaled giant planet entry testing is beyond the simulation capability of most impulse facilities, which limits the ground testing data available for computational model validation. Substituting the He in their predominately H\(_2\)/He atmospheres with Ne has been used in the previous experiments. This enables higher-temperature shock layers to be recreated using the same facility performance. For binary hydrogen dissociation and ionization reactions, the substitution gives similarity with non-equilibrium processes, but has never been experimentally validated by direct comparison with H\(_2\)/He relaxation data in a region where the facility simulation capabilities in using H\(_2\)/He and H\(_2\)/Ne overlap. This work demonstrates and validates a scaling method based on the substitution in terms of flow relaxation. A H\(_2\)/Ne condition was designed to recreate the post-shock relaxation of a H\(_2\)/He condition in our X2 expansion tube. The two conditions were experimentally tested with cylindrical test models, and shock layer radiation from the Balmer series was measured. The spectroscopic data using the H\(_2\)/Ne condition show a successful recreation of the non-equilibrium processes of the target H\(_2\)/He condition, experimentally validating the scaling method. High-speed images demonstrate that the associated radiation field is also correctly reproduced. With the use of this substitution, the facility can now be used to simulate high-speed giant planet entries with confidence, and the available ground testing envelope is extended to much higher speeds.
Similar content being viewed by others
Abbreviations
- r :
-
Mole fraction of H\(_2\)
- \({[}{\text {M}}{]}\) :
-
Molar concentration of species M, mol/m\(^3\)
- P :
-
Pressure, Pa
- T :
-
Temperature, K
- \(K_{\text {fd}}\) :
-
Forward dissociation rate coefficient, \(\hbox {m}^{3} \; \hbox {s}^{-1} \; \hbox { mol}^{-1}\)
- \(\alpha\) :
-
Mole fraction of dissociated H\(_2\)
- V :
-
Velocity, m/s
- \(\chi\) :
-
Binary scaling variable, \(\int \frac{P}{V} {\text {d}}x\), Pa s
- \(K_{\text {fi}}\) :
-
Forward ionization rate coefficient, \(\hbox {m}^{3}\; \hbox {s}^{-1} \; \hbox {mol}^{-1}\)
- \(\beta\) :
-
Mole fraction of ionized H
- \(\rho\) :
-
Density, kg/m\(^3\)
- f:
-
Post-shock frozen state
- i:
-
Initial ionizing (fully dissociated) state
References
Canny John (1986) A computational approach to edge detection, PAMI. IEEE Trans Pattern Anal Mach Intell 8(6):679–698
Capra Bianca R, Morgan Richard G (2013) Total heat transfer measurements on a flight investigation of reentry environment model. J Spacecr Rockets 50(3):494–503
Cruden BA, Bogdanoff DW (2017) Shock radiation tests for Saturn and Uranus entry probes. J Spacecr Rockets 54(6):1246–1257
de Crombrugghe G, Morgan R, Chazot O (2016) Theoretical approach and experimental verification of the role of diffusive transport under binary scaling conditions. Int J Heat Mass Transf 97:675–682. https://doi.org/10.1016/j.ijheatmasstransfer.2016.02.018
ESA (2005) Cassini–Huggens. http://sci.esa.int/cassini-huygens/33006-engineering/?fbodylongid=1151. Accessed 11 May 2019
Erb AJ, West TK, Johnston CO (2020) Investigation of Galileo probe entry heating with coupled radiation and ablation. J Spacecr Rockets 57(4):692–706
Gildfind DE, James CM, Toniato P, Morgan RG (2015) Performance considerations for expansion tube operation with a shock-heated secondary driver. J Fluid Mech 777:364–407
Gildfind DE, Morgan RG, Jacobs PA (2016) Expansion tubes in Australia. In: Igra O, Seiler F (eds) Experimental methods of shock wave research. Springer, Cham, pp 399–431
Gildfind DE, Morgan RG, McGilvray M, Jacobs PA, Stalker RJ, Eichmann TN (2011) Free-piston driver optimisation for simulation of high mach number scramjet flow conditions. Shock Waves 21(6):559–572
Gordon G, McBride BJ (1994) Computer program for calculation of complex chemical equilibrium compositions and applications I. analysis. NASA Lewis Research Center, Cleveland, OH, USA
Gollan R, Jacobs P (2013) About the formulation, verification and validation of the hypersonic flow solver Eilmer. Int J Numer Meth Fluids 73(1):19–57. https://doi.org/10.1002/fld.3790
Higgins CE (2004) Aerothermodynamics of the gas giants. PhD thesis, the University of Queensland, Brisabane, Australia
Jacobs P, Gollan R (2016) Implementation of a Compressible-Flow Simulation Code in the D Programming Language. Advances of Computational Mechanics in Australia, Applied Mechanics and Materials, Trans Tech Publications Ltd, 46:54–60. https://doi.org/10.4028/www.scientific.net/AMM.846.54
James CM, Cullen TG, Wei H, Lewis SW, Gu S, Morgan RG, McIntyre TJ (2018) Improved test time evaluation in an expansion tube. Exp Fluids 59:87
James CM, Gildfind DE, Lewis SW, Morgan RG, Zander F (2018) Implementation of a state-to-state analytical framework for the calculation of expansion tube flow properties. Shock Waves 28(2):349–377
James Christopher M, Gildfind David E, Morgan Richard G, Lewis Steven W, McIntyre Timothy J (2019) Simulating gas giant atmospheric entry using helium and neon test gas substitutions. J Spacecr Rockets 56(3):725–743
James CM, Liu Y, Morgan R (2020) Simulating Uranus entry in an expansion tube. In: AIAA aviation 2020 forum, virtual event
James CM (2017) Radiation from simulated atmospheric entry into the gas giants. PhD thesis, the University of Queensland, Brisabane, Australia
Jits R, Wright M, Chen Y-K (2005) Closed-loop trajectory simulation for thermal protection system design for Neptune aerocapture. J Spacecr Rockets 42:1025–1034
Laux CO (1993) Optical diagnostics and radiative emission of air plasmas. PhD thesis, Stanford University
Lewis SW, James CM, Morgan RG, McIntyre TJ, Alba CR, Greendyke RG (2017) Carbon ablative shock-layer radiation with high surface temperatures. J Thermophys Heat Transf 31(1):193–204
Liu Y, James CM, Morgan RG, McIntyre TJ (2020) Using aerothermodynamic similarity to experimentally study nonequilibrium giant planet entry. J Spacecr Rockets 1–13
Matsuyama Shingo, Ohnishi Naofumi, Sasoh Akihiro, Sawada Keisuke (2005) Numerical simulation of Galileo probe entry flowfield with radiation and ablation. J Thermophys Heat Transf 19(1):28–35
McBride BJ, Gordon G (1996) Computer program for calculation of complex chemical equilibrium compositions and applications II. Users manual and program description. NASA Lewis Research Center, Cleveland, OH, USA
Milos FS (1997) Galileo probe heat shield ablation experiment. J Spacecr Rockets 34:705–713
Milos FS, Chen Y-K, Squire TH, Brewer RA (1999) Analysis of Galileo probe heatshield ablation and temperature data. J Spacecr Rockets 36(3):298–306
Moss J, Simmonds A (1982) Galileo probe forebody flowfield predictions during Jupiter entry. In: 3rd joint thermophysics, fluids, plasma and heat transfer conference
Niemann Hasso B, Atreya Sushil K, Carignan George R, Donahue Thomas M, Haberman John A, Harpold Dan N, Hartle Richard E, Hunten Donald M, Kasprzak Wayne T, Mahaffy Paul R, Owen Tobias C, Spencer Nelson W, Way Stanley H (1996) The Galileo probe mass spectrometer: composition of Jupiter’s atmosphere. Science 272(5263):846–849
Palmer G, Prabhu D, Cruden BA (2014) Aeroheating uncertainties in Uranus and Saturn entries by the Monte Carlo method. J Spacecr Rockets 51:801–814
Park Chul (2009) Stagnation-region heating environment of the Galileo probe. J Thermophys Heat Transf 23(3):417–424
Park C, Tauber M (1999) Heatshielding problems of planetary entry—a review. In: 30th fluid dynamics conference
Ravichandran Ranjith, Buttsworth David R, Lewis Steven W, Morgan Richard G, McIntyre Timothy J (2019) Filtered image thermography for high temperatures in hypersonic preheated ablation experiments. J Thermophys Heat Transf 33(4):1074–1084
Santos Fernandes L, Lopez B, da Silva M Lino (2019) Computational fluid radiative dynamics of the Galileo Jupiter entry. Phys Fluids 31(10):106104
Sayanagi KM, Dillman RA, Atkinson DH, Li J, Saikia AA, Simon S, Spilker MH, Wong TR, Edwards WC, Hope D, Arora A, Bowen SC, Bowes A, Brady JS, Clark TO, Fairbairn RE, Goggin DG, Grondin TA, Horan SJ, Infeld SI, Leckey JP, Longuski JM, Marvel TE, McCabe RM, Parikh AM, Peterson DJ, Primeaux SJ, Scammell AD, Somervill KM, Taylor LW, Thames C, Tosoc HP, Tran LD (2020) Small next-generation atmospheric probe (snap) concept to enable future multi-probe missions: a case study for uranus. Space Sci Rev 216(72):1–47
Stalker RJ (1980) Shock tunnel measurement of ionization rates in hydrogen. AIAA J 18(4):478–480
Stalker RJ, Edwards BP (1998) Hypersonic blunt-body flows in hydrogen-neon mixtures. J Spacecr Rockets 35:729–735
von Zahn U, Hunten DM (1996) The helium mass fraction in Jupiter’s atmosphere. Science 272(5263):849–851
Acknowledgements
The authors would like to thank Mr. Neil Duncan for the model manufacturing, as well as and the operators for X2 for keeping the facility running well. We are grateful to Dr. Peter Jacobs and Dr. Rowan Gollan for their help in the use of Poshax, and to Prof. David Mee for insightful discussions. The spectral analysis code developed by Dr. Steven Lewis is also gratefully acknowledged.
Funding
This research was supported by Australian Research Council.
Author information
Authors and Affiliations
Corresponding author
Ethics declarations
Conflict of interest
The authors declare that they have no conflict of interest.
Additional information
Publisher's Note
Springer Nature remains neutral with regard to jurisdictional claims in published maps and institutional affiliations.
Rights and permissions
About this article
Cite this article
Liu, Y., James, C.M., Morgan, R.G. et al. Experimental validation of a test gas substitution for simulating non-equilibrium giant planet entry conditions in impulse facilities. Exp Fluids 61, 198 (2020). https://doi.org/10.1007/s00348-020-03032-3
Received:
Revised:
Accepted:
Published:
DOI: https://doi.org/10.1007/s00348-020-03032-3