Compiling the RN dimensionless number to determine the boundary between aerothermodynamics and radiation heating for ablative noses

Authors

1 Department of Mechanic- Energy Conversion Engineering, Azad University, West Tehran, Iran.

2 Faculty of Aerospace, Malek Ashtar University of Technology, Iran.

3 Department of Mechanic Engineering, Azad University, West Tehran, Iran.

10.22044/jsfm.2024.13655.3797

Abstract

The abstract should be written with 100 to 200 words (Times New Roman 9). The most complete method to calculate aerothermodynamics and radiation heating applied to the walls of the hypersonic destructible is simultaneous solution of flow equations, chemical reaction kinetics, combustion model in the destructible layer, radiation models and flow turbulence. Using this algorithm over time requires a high amount of computing memory. Due to the high solution time, the users of this code do not consider it reasonable to use it for preliminary design purposes. Therefore, the aim of this research is to compile the dimensionless number RN by using the results of CTCA code and Buckingham's method to determine the boundary between aerothermodynamics and radiation heating in order to reduce the solution time related to CTCA code, so that in RN smaller than 1.0, it is possible to calculate the heating ignore radiation versus aerothermodynamics heating and disable the subroutine related to radiation heating, and also in RN greater than 2.0, you can ignore aerothermodynamics heating versus radiation heating and disable the subroutine related to aerothermodynamics heating. By considering these changes on CTCA code, its solution time for a nose with a typical flight envelope was reduced by 15%, the maximum amount of error in the total heat flux compared to CTCA code was less than 2%. It should be noted that in the1≤RN≤2, the effects of aerothermodynamics and radiation heating should be considered simultaneously and the relevant subroutines in CTCA code should be activated.

Keywords

Main Subjects

References

[1] J. Anderson (1989) Hypersonic and High Temperature Gas Dynamics, Second Edittion, pp. 25-346, New York: ISBN:978-964-2751-04-4.
[2] M. M. Doustar, M. Mardani, F. Ghadak (2017) Aero-heating Modelling on the Ablative Noses during Flight Trajectory, Aircraft Engineering and Aerospace Tech. J., Vol. 8, No. 3, pp.52-70.
[3] A. Kumar (1980) Laminar and Turbulent Flow Solutions with Radiation and Ablation Injection for Jovian Entry, AIAA J., Vol. 12, No. 3, pp.30-41.
[4] K. Sutton (1985) Air Radiation Revisited, in Thermal Design of Aeroassisted Orbital Transfer Vehicles, AIAA Progress in Astronautics and Aernautics Series, Vol. 96, pp. 419-441.
[5] R. J. Gollan (2011) Numerical Modeling of Radiating Supraorbital Flows, The University of Queensland Brisbane 4072, Australia.
[6] D. F. Potter (2011) Modeling of radiating shock layers for atmospheric entry at Earth and Mars, Scientaa AC Abore, Vol. 34, pp. 320-341.
[7] S. Benjamin, H. Roy, H.S. Paul, T. Baumanb,and T. A. Oliver (2014) Modeling hypersonic entry with the fully-implicit Navier–Stokes (FIN-S) stabilized finite element flow solver Computers & Fluids, pp. 281–292.
[8] M. M. Doustar, M. Mardani, F. Ghadak (2016) Simulation of temperature distribution for hypersonic ablative noses during flight trajectory by space marching method, Modares Mechanical Engineering, Vol. 16, No. 12, pp. 163-174 (in Persian).
[9] M. M. Doustar, M. Mardani, F. Ghadak (2019) Investigation of the catalytic wall effect on the aerothermodynamics heating of ablative noses by space marching method, Fluid mechanic and aerodynamic J. Imam hossien Univ., Vol. 4, No. 2, pp. 40-50 (in Persian).
 
[10] M. M. Doustar, M. Mardani, F. Ghada (2017) Numerical simulation of radiance effects on the aerodynamic heating of ablative nose with VSL-VBLS method, Struct. Fluid J. Shahrod Univ., Vol. 5, No. 3, pp. 10-27 (in Persian).
[11] Y, Tao., Z, Wuli., Q, Han (2019) Theory of Aerodynamic heating from molecular collision analysis, J. Phys. Let. A, Vol. 384, No. 4.
[12] J, Zhang., J, Guangchen (2020) Recent advances in the application of advanced algorithms in computational dynamics technology, Int. J. a Aerospace Eng., Vol. 32, No. 5.
[13] L, Qi., L, Junhong., Z, Jingyun (2021)Thermal Environment and Aeroheating Mechanism of Protuberances of Mars Entry Capsule, J. Space Sci. Tech., Vol. 28, No. 12.
[14] R, Renane.,R, Allouche (2022) Aeroheating optimization of a hypersonic thermochemical non equilibrium around blunt body by application of opposing Jet and Blunt Spike, Hypersonic Vehicles Books.
[15] E.W. Miner, Computer User’s (1975) Guide for a Chemically Reacting Viscous Shock Layer Code, NASA CR-2551, pp.24-32.
[16] G. Irina, C. Brykina, D. Scott (1998) An Approximate Axisymmetric Viscous Shock Layer Aeroheating Method for Three-Dimensional Bodies, AIAA NASA, TM198-207890, pp.14-22.
[17] G.R. Dexygen1.6.1 (2012) Ablation Modeling of Nose Section with UDF Linkage to Fluent Software. J. Thermophys.Heat Trans., Vol. 14, No. 3, pp. 32-41.
[18] J.D. Marvin (1983) Turbulence Modeling for Computational Aerodynamics, AIAA J., Vol. 21,  No. 7, pp. 941-955.
[19] Abdolahi Poor, S., Mardani, A., & Seyed ShamsTaleghani, S. A. (2016). Effects of pulsed counter flow jets on aerothermodynamics performance of a Re-Entry capsule at supersonic flow. Aero. Knoldge. Tech. J., 5(1), 55-65.
[20] Abdolahi, S., Etemadi, F., & Ebrahimi, M. (2015). Aerodynamic Heating Prediction of Flying Body Using Fluid-Solid Conjugate Heat Transfer. Space Science and Technology, 8(3).
Journal of Solid and Fluid Mechanics
Volume 14, Issue 1
March and April 2024
Pages 127-138

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