CO2 number density measurement in a shock tube with preheated carbon surface

The interaction between a heated carbon-based material and high-temperature air may produce ablation gas species such as CO2, affecting heat transfer onto the surface of a thermal protection system. The prediction of ablation gas production is critical for heat flux prediction and the design of a thermal protection system. In this study, we present a system that measures the number density of CO2 formed by the gas–surface interaction between a hot carbon surface and high-temperature gas. The heated carbon wall is exposed to high-temperature air by using a shock tube and surface heating model. The surface temperature of the carbon wall is measured using two-color ratio pyrometry. The number density of CO2 is predicted by performing numerical calculations for the shock tube flow with gas–surface interaction modeling. The number density of CO2 molecules is measured using infrared emission spectroscopy. The measured CO2 number density is 9.60 × 1023 m−3 at an area-weighted average surface temperature of 1212 K. The measured number density matches the predicted value within an error of 6%. The proposed system is applicable for CO2 number density measurement under various gas–surface interaction conditions, and it can be used for the investigation of ablative gas production and numerical research on gas–surface interactions.

[1]  Jae Gang Kim,et al.  Stagnation-point heating and ablation analysis of orbital re-entry experiment , 2021, Physics of Fluids.

[2]  Xiaofeng Yang,et al.  Heat transfer with interface effects in high-enthalpy and high-speed flow: Modelling review and recent progress , 2021 .

[3]  G. Park,et al.  Temperature measurement of carbon dioxide using emission spectroscopy , 2020 .

[4]  G. Park,et al.  Thermochemical nonequilibrium flow analysis in low enthalpy shock-tunnel facility , 2020, PloS one.

[5]  G. Park,et al.  Effect of titanium surface roughness on oxygen catalytic recombination in a shock tube , 2020 .

[6]  G. Park,et al.  Experimental and numerical study of oxygen catalytic recombination of SiC-coated material , 2019, International Journal of Heat and Mass Transfer.

[7]  G. Park,et al.  Experimental study of oxygen catalytic recombination on a smooth surface in a shock tube , 2019, Applied Thermal Engineering.

[8]  G. Park,et al.  Temperature determination in a shock tube using hydroxyl radical A-X band emission , 2019, Physics of Fluids.

[9]  Y. Bondar,et al.  Surface recombination in the direct simulation Monte Carlo method , 2018, Physics of Fluids.

[10]  G. Park,et al.  Thermochemical nonequilibrium parameter modification of oxygen for a two-temperature model , 2018 .

[11]  M. Mancini,et al.  Absorption of infrared radiation by carbon monoxide at elevated temperatures and pressures: Part A. Advancing the line-by-line procedure based on HITEMP-2010 , 2017 .

[12]  C. Laux,et al.  Infrared spectroscopic measurements of carbon monoxide within a high temperature ablative boundary layer , 2016 .

[13]  Weijie Li,et al.  A new mechanism of surface ablation of charring materials for a vehicle during reentry , 2016 .

[14]  Fabio Gori,et al.  Theoretical prediction of thermal conductivity for thermal protection systems , 2012 .

[15]  A. Soufiani,et al.  Updated band model parameters for H2O, CO2, CH4 and CO radiation at high temperature , 2012 .

[16]  Andrey V. Veniaminov,et al.  Calibration of the spectral sensitivity of instruments for the near infrared region , 2011 .

[17]  Philippe Rivière,et al.  Spectroscopic data for the prediction of radiative transfer in CO2–N2 plasmas , 2009 .

[18]  Peter A. Gnoffo,et al.  The Influence of Ablation on Radiative Heating for Earth Entry , 2008 .

[19]  J. L. Stollery,et al.  Hypersonic and High-Temperature Gas Dynamics – Second edition J.D. Anderson American Institute of Aeronautics and Astronautics, 1801 Alexander Bell Drive, Suite 500, Reston, VA, USA. 20191-4344. 2006. 811pp. Illustrated. $64.95 (AIAA members), $90.95 (non-members). ISBN 1-56347-780-7. , 2007, The Aeronautical Journal (1968).

[20]  R. Ferencz,et al.  Comparison of Surface Chemical Kinetic Models for Ablative Reentry of Graphite , 2002 .

[21]  R. Gupta,et al.  Aerothermodynamic Analysis of Stardust Sample Return Capsule With Coupled Radiation and Ablation , 1999 .

[22]  S. V. Zhluktov,et al.  Viscous Shock-Layer Simulation of Airflow past Ablating Blunt Body with Carbon Surface , 1999 .

[23]  Michael E. Tauber,et al.  AEROTHERMODYNAMICS OF THE STARDUST SAMPLE RETURN CAPSULE , 1998 .

[24]  A. N. Syverud,et al.  JANAF Thermochemical Tables, 1982 Supplement , 1982 .

[25]  G. Sutton,et al.  Spectral emissivity measurements of ablating phenolic graphite. , 1969 .

[26]  N. Diaconis,et al.  Oxidation and sublimation of graphite in simulated re-entry environments. , 1967 .

[27]  D. E. Rosner,et al.  High-temperature kinetics of graphite oxidation by dissociated oxygen , 1965 .

[28]  V. Oinas,et al.  Atmospheric Radiation , 1963, Nature.

[29]  H. Eyring,et al.  Kinetics of Graphite Oxidation , 1957 .

[30]  O. C. Simpson,et al.  Spectral Emissivities of Graphite and Carbon , 1953 .