16 Uncertainty Treatment Applications: High-Enthalpy Flow Ground Testing
537
The stagnation point material recession was less than predicted but the recession
in the afterbody region was much higher than expected. In this case, the physical
phenomena was not well-captured by the simulation tools.
The policy of safety margins must be replaced by state-of-the-art uncertainty
quantification techniques for predictive engineering with benefits for the design
without compromising the safety of the mission.
Acknowledgments The authors thank the European Commission H2020 programme, through the
UTOPIAE Marie Curie Innovative Training Network, H2020-MSCA-ITN-2016, Grant Agreement
number 722734.
References
1. O. Chazot, F. Panerai, High enthalpy facilities and plasma wind tunnels for aerothermodynamics ground testing, in Nonequilibrium Hypersonic Flows, ed. by E. Josyula (ARLF, 2015)
2. R.D. Neumann, Experimental methods for hypersonics: capabilities and limitations, in Second
Joint Europe-US Short Course on Hypersonic: GAMNI-SMAI and University of Texas at Austin
(USAF Academy, Colorado, 1989)
3. N.C. Freeman, Non equilibrium flow of an ideal dissociating gas. J. Fluid Mech. 4(4), 407–442
(1958)
4. W.E. Gibson, P.V. Marrone, A similitude for non-equilibrium phenomena in hypersonic flight.
in The High Temperature Aspect of Hypersonic Flow, AGARDograph 69, ed. by W.C. Nelson
(Pergamon Press, Oxford, 1964)
5. G.R. Inger, C. Higgins, R. Morgan, Generalized nonequilibrium binary scaling for shock
standoff on hypersonic blunt bodies. J. Thermophys. Heat Transf. 17(1), 126–128 2003
6. A.F. Kolesnikov, Extrapolation from high enthalpy tests to flight based on the concept of local
heat transfer simulation, in RTO Educational Notes on Measurement Techniques for High
Enthalpy and Plasma Flows (Rhode-St-Genese 1999)
7. P.F. Barbante, O. Chazot, Flight extrapolation of plasma wind tunnel stagnation region
flowfield. J. Thermophys. Heat Transf. 20(3), 493–499 (2006)
8. J.B. Scoggins, Development of Numerical Methods and Study of Coupled Flow, Radiation,
and Ablation Phenomena for Atmospheric Entry. Ph.D. thesis, CentraleSupelec/VKI, 2017
9. R. Goulard, On catalytic recombination rates in hypersonic stagnation heat transfer. Jet
Propulsion 28(11), 737–745 (1958)
10. F. Panerai, Aerothermochemistry Characterization of Thermal Protection Systems. Ph.D.
thesis, Universita degli Studi di Perugia/VKI, 2012
11. A. Viladegut, O. Chazot, Enthalpy characterization and assessment of copper catalysis
determination in inductively coupled plasma facility, in 45th AIAA Thermophysics Conference,
AIAA AVIATION Forum, (AIAA 2015-3107) (2015)
12. R.K. Crouch, G.D. Walberg, An Investigation of Ablation Behavior of Avcoat 5026/39M Over
a Wide Range of Thermal Environments. Technical Memorandum TM X-1778, NASA, 1969.
16, 21, 36
13. B.H. Wick, Ablation characteristics and their evaluation by means of arc jets and arc radiation
sources, in Secenth International Aeronautical Congress (Paris, 1965)
14. N.K. Hiester, C.F. Clark, Comparative Evaluation of Ablating Materials in Arc Plasma Jets.
NASA Contractor Report CR-1207, Stanford Research Institute/NASA, 1968
15. M.A. Covington, J.M. Heinemann, H.E. Goldstein, Y.K. Chen, I. Terrazas-Salinas, J.A.
Balboni, J. Olejniczak, E.R. Martinez, Performance of a low density ablative heat shield
material. J. Space Craft Rock. 45(4), 854–864 (2008)
537
The stagnation point material recession was less than predicted but the recession
in the afterbody region was much higher than expected. In this case, the physical
phenomena was not well-captured by the simulation tools.
The policy of safety margins must be replaced by state-of-the-art uncertainty
quantification techniques for predictive engineering with benefits for the design
without compromising the safety of the mission.
Acknowledgments The authors thank the European Commission H2020 programme, through the
UTOPIAE Marie Curie Innovative Training Network, H2020-MSCA-ITN-2016, Grant Agreement
number 722734.
References
1. O. Chazot, F. Panerai, High enthalpy facilities and plasma wind tunnels for aerothermodynamics ground testing, in Nonequilibrium Hypersonic Flows, ed. by E. Josyula (ARLF, 2015)
2. R.D. Neumann, Experimental methods for hypersonics: capabilities and limitations, in Second
Joint Europe-US Short Course on Hypersonic: GAMNI-SMAI and University of Texas at Austin
(USAF Academy, Colorado, 1989)
3. N.C. Freeman, Non equilibrium flow of an ideal dissociating gas. J. Fluid Mech. 4(4), 407–442
(1958)
4. W.E. Gibson, P.V. Marrone, A similitude for non-equilibrium phenomena in hypersonic flight.
in The High Temperature Aspect of Hypersonic Flow, AGARDograph 69, ed. by W.C. Nelson
(Pergamon Press, Oxford, 1964)
5. G.R. Inger, C. Higgins, R. Morgan, Generalized nonequilibrium binary scaling for shock
standoff on hypersonic blunt bodies. J. Thermophys. Heat Transf. 17(1), 126–128 2003
6. A.F. Kolesnikov, Extrapolation from high enthalpy tests to flight based on the concept of local
heat transfer simulation, in RTO Educational Notes on Measurement Techniques for High
Enthalpy and Plasma Flows (Rhode-St-Genese 1999)
7. P.F. Barbante, O. Chazot, Flight extrapolation of plasma wind tunnel stagnation region
flowfield. J. Thermophys. Heat Transf. 20(3), 493–499 (2006)
8. J.B. Scoggins, Development of Numerical Methods and Study of Coupled Flow, Radiation,
and Ablation Phenomena for Atmospheric Entry. Ph.D. thesis, CentraleSupelec/VKI, 2017
9. R. Goulard, On catalytic recombination rates in hypersonic stagnation heat transfer. Jet
Propulsion 28(11), 737–745 (1958)
10. F. Panerai, Aerothermochemistry Characterization of Thermal Protection Systems. Ph.D.
thesis, Universita degli Studi di Perugia/VKI, 2012
11. A. Viladegut, O. Chazot, Enthalpy characterization and assessment of copper catalysis
determination in inductively coupled plasma facility, in 45th AIAA Thermophysics Conference,
AIAA AVIATION Forum, (AIAA 2015-3107) (2015)
12. R.K. Crouch, G.D. Walberg, An Investigation of Ablation Behavior of Avcoat 5026/39M Over
a Wide Range of Thermal Environments. Technical Memorandum TM X-1778, NASA, 1969.
16, 21, 36
13. B.H. Wick, Ablation characteristics and their evaluation by means of arc jets and arc radiation
sources, in Secenth International Aeronautical Congress (Paris, 1965)
14. N.K. Hiester, C.F. Clark, Comparative Evaluation of Ablating Materials in Arc Plasma Jets.
NASA Contractor Report CR-1207, Stanford Research Institute/NASA, 1968
15. M.A. Covington, J.M. Heinemann, H.E. Goldstein, Y.K. Chen, I. Terrazas-Salinas, J.A.
Balboni, J. Olejniczak, E.R. Martinez, Performance of a low density ablative heat shield
material. J. Space Craft Rock. 45(4), 854–864 (2008)