Influence of chemical models on heat flux for EXPERT and Orion capsules

The computation of heat flux on two current re-entry capsules, European eXPErimental Reentry Testbed (EXPERT) and Orion, has been carried out by a direct simulation Monte Carlo code (DS2V) and by a computational fluid dynamic code (H3NS) in transitional regime, considering both non-reactive and fully catalytic surface. These capsules have been chosen for this analysis because they have been characterized by completely different shapes and re-entry trajectories. DS2V and H3NS use the Gupta and the Park chemical models, respectively. The results showed that the heat flux predicted by DS2V is always higher than that predicted by H3NS. Therefore, a sensitivity analysis of the chemical models on the heat flux has been carried out for both capsules. More specifically, the Park model has been implemented in DS2V as well. The results showed that DS2V and H3NS compute a different chemical composition both in the flow field and on the surface, even when using the same chemical model (Park); therefore, the different results obtained from the two codes can be attributed mostly to the different methodology used in handling all chemical processes.

[1]  Harry Partridge,et al.  Chemical-kinetic parameters of hyperbolic Earth entry , 2000 .

[2]  Richard A. Thompson,et al.  A review of reaction rates and thermodynamic and transport properties for the 11-species air model for chemical and thermal nonequilibrium calculations to 30000 K , 1989 .

[3]  C. Shen Rarefied Gas Dynamics: Fundamentals, Simulations and Micro Flows , 2005 .

[4]  Gennaro Zuppardi,et al.  Analysis of Aero‐Thermodynamic Behavior of EXPERT Capsule in Transitional Regime , 2011 .

[5]  Iain D. Boyd,et al.  Modeling backward chemical rate processes in the direct simulation Monte Carlo method , 2007 .

[6]  Francis A. Greene,et al.  Orion Aerodynamics for Hypersonic Free Molecular to Continuum Conditions , 2013 .

[7]  E Glass Christopher,et al.  Aerothermodynamic Characteristics in the Hypersonic Continuum-Rarefied Transitional Regime , 2001 .

[8]  Pavel Vashchenkov,et al.  Numerical Investigation of the EXPERT Reentry Vehicle Aerothermodynamics Along the Descent Trajectory , 2007 .

[9]  J. R. Torczynski,et al.  Convergence behavior of a new DSMC algorithm , 2009, J. Comput. Phys..

[10]  Antonio Schettino,et al.  Hypersonic Low-Density Aerothermodynamics of Orion-Like Exploration Vehicle , 2009 .

[11]  Mikhail Naumovich Kogan,et al.  Rarefied Gas Dynamics , 1969 .

[12]  Graeme A. Bird,et al.  The DS2V/3V Program Suite for DSMC Calculations , 2005 .

[13]  Peter A. Gnoffo,et al.  Conservation equations and physical models for hypersonic air flows in thermal and chemical nonequilibrium , 1989 .

[14]  Michail A. Gallis,et al.  Accuracy and efficiency of the sophisticated direct simulation Monte Carlo algorithm for simulating noncontinuum gas flows , 2009 .

[15]  Chul Park,et al.  Validation of multi-temperature nozzle flow code NOZNT , 1993 .

[16]  James N. Moss Rarefied Flows of Planetary Entry Capsules , 1997 .