THERMAL SCIENCE

International Scientific Journal

Fei Zhao

,

Lanhai Su

,

Rong ZhuORCID

,

Zhihui LiORCID

STUDY OF LINEAR ABLATIVE RATE OF D6AC STEEL WING USED ON SUPERSONIC MISSILE

ABSTRACT
The D6AC steel wing used on supersonic missile is the object in this study. Its service environment was generated and simulated. The ablation experiment of D6AC steel missile wing was carried out under different parameters of flow field. The ablation process of D6AC steel wing was studied and analyzed under the supersonic aerodynamic heating environment. The results show that the ablation process of D6AC steel missile wing could be divided into three stages: aerodynamic heating, oxidation reaction and shear stripping. The influence factors of the D6AC steel wing ablation include the total temperature, Mach number, oxygen content and water content. The higher the total temperature is, the more early the initial ablation time of wing is. The linear ablative rate of the D6AC steel wing is the result of the interaction of the Mach number, oxygen content and water content. The higher the Mach number is, the larger the oxygen content is, and the larger the linear ablative rate of missile wing is. The influence of water content on the linear ablative rate of D6AC steel wing is the opposite.
KEYWORDS
supersonic jet, flow field parameters, linear ablative rate, D6AC steel, missile wing
PAPER SUBMITTED: 2018-09-10
PAPER REVISED: 2018-11-19
PAPER ACCEPTED: 2018-11-21
PUBLISHED ONLINE: 2018-12-16
DOI REFERENCE: https://doi.org/10.2298/TSCI180910323Z
CITATION EXPORT: view in browser or download as text file
THERMAL SCIENCE YEAR 2019, VOLUME 23, ISSUE No. 6, PAGES [4107 - 4116]
REFERENCES
[1] Van Driest, E. R., The Problem of Aerodynamic Heating, Aeronautical Engineering Review, 15 (1956),10, pp. 26-41
[2] Wurster, K. E., Stone, H. W., Aerodynamic Heating Environment Definition/Thermal Protection System Selection for the HL-20, Journal of Spacecraft Rockets, 30 (1993), 5, pp. 549-557, 10.2514/3.25565
[3] Mahulikar, S. P., Theoretical Aerothermal Concepts for Confguration Design of Hypersonic Vehicles, Aerospace Science and Technology, 9 (2005), 8, pp. 681-685
[4] Cayzac, R., et al., Navier-Stokes Computation of Heat Transfer and Aero-Heating Modeling for Supersonic Projectiles, Aerospace Science and Technology, 10 (2006), 5, pp. 374-384, 10.1016/j.ast.2005.12.001
[5] Kostoff, R. N., Cummings, R. M., Highly Cited Literature of High-Speed Compressible Flow Research, Aerospace Science and Technology, 26 (2013), 1, pp. 216-234, 10.1016/j.ast.2012.04.006
[6] Bao, W., et al., Effect of Structural Factors on Maximum Aerodynamic Heat Flux of Strut Leading Surface, Applied Thermal Engineering, 69 (2014), 1, pp. 188-198, 10.1016/j.applthermaleng.2013.11.068
[7] Liu, L. G., Zhou, L., Sun, H., Aerodynamic Thermal Elasticity Analysis of Wing Structure of Supersonic Speed Missile. Sichuan Ordnance Journal, 5 (2015), pp. 28-34
[8] Ognjanovic, O., Maksimovic, S., Vidanovic, N., et al., Numerical aerodynamic-thermal-structural analyses of missile fin configuration during supersonic flight conditions. Thermal Science, 21 (2016), 6B, pp. 3037-3049, 10.2298/tsci160919318o
[9] Qi, Y. W., Aerodynamics and Aerodynamic heating Research for the Wing of Hypersonic Projectil, M.S. thesis, Nanjing University of Science and Technology, Nanjing, China, 2017
[10] Huang, Y. C., Aerodynamic Anslysis and Ballistic Simulation about Hypersonic Projectile, M.S. thesis, Nanjing University of Science and Technology, Nanjing, China, 2017
[11] Shi, J. G., The Study of aerodynamic ablation for hypersonic projectile wing and numerical calculation, M.S. thesis, Nanjing University of Science and Technology, Nanjing, China, 2002
[12] VERSTEEG, H. K., MALALASEKERA, W., An introduction to computational fluid dynamics: the finite volume method. Pearson Education Inc., New York, USA, 2007, 10.1016/b978-0-32-399544-3.00013-x
[13] WILCOX, D. C., Turbulence modeling for CFD, DCW Industries Inc., La Canada, CA, 1998
[14] BALABEL, A., HEGAB, A. M., NASR, M., et al. Assessment of turbulence modeling for gas flow in two-dimensional convergent-divergent rocket nozzle. Applied Mathematical Modelling, 35 (2011), 7, pp. 3408-3422
[15] MENTER, F. R., Two-equation eddy-viscosity turbulence models for engineering applications. AIAA Journal, 32 (1994), 8, pp. 1598-1605, 10.2514/3.12149
[16] ANDERSON, J. D., WENDT, J., Computational fluid dynamics. McGraw-Hill Inc., New York, USA, 1995
[17] ZHANG, D. L., A course in computional fluid dynamics. Higher Educiation Press, Beijing, China, 2010
[18] Zhang, Z. C., Hypersonic aerodynamic heat and heat protection. National Defense Industry Press, Beijing, China, 2003
[19] Jiang, G. Q., Liu, L. Y., Heat transfer of hypersonic gas and ablation thermal protection. National Defense Industry Press, Beijing, China, 2003
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Study of linear ablative rate of D6AC steel wing used on supersonic missile

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