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Optimization of artillery projectiles base drag reduction using hot base flow

ABSTRACT
The computational fluid dynamics (CFD) numerical simulations were carried out to investigate the base drag characteristics of a projectile with base bleed unit with a central jet. Different base bleed grain types with different combustion temperatures were used. The goal was to find a way to effectively control the base flow for base drag reduction and optimisate the latter using an adequate (CFD) software. Axisymmetric, compressible, mass-averaged Navier-Stokes equations are solved using the k-ω SST, transition k-kl-ω and RSM turbulence models. The various base flow characteristics are obtained by the change in the non-dimensionalized injection impulse. The results obtained through the present study show that there is an optimum bleed condition for all base bleed grains tested. That optimum is dependent on the temperature of the grain combustion products. The optimum reduces the total drag for 6,9% in the case of air injection at temperature of 300K and reaches up to 28% in the case of propellant combustion products injection at almost 2500K. Besides, the increasing of molecular wight has a role no less important than temperature of the combustion products in terms of base drag reduction.
KEYWORDS
PAPER SUBMITTED: 2018-04-13
PAPER REVISED: 2018-07-06
PAPER ACCEPTED: 2018-07-18
PUBLISHED ONLINE: 2018-09-30
DOI REFERENCE: https://doi.org/10.2298/TSCI180413210D
REFERENCES
  1. Sahu, J., Supersonic flow over cylindrical afterbodies with base bleed, Computational Mechanics, 2 (1987) 3, pp.176-184. doi.org/10.1007/BF00571023
  2. Viswanath, P. R., Flow management techniques for base and afterbody drag reduction. Progress in Aerospace Sciences, 32 (1996), 2-3, pp. 79-129. doi.org/10.1016/0376-0421(95)00003-8
  3. Lee, Y., Kim. H. -D. , Optimization of mass bleed control for base drag reduction of supersonic flight bodies. Journal of Thermal Science, 15 (2006), 3, pp. 206-212. doi.org/10.1007/s11630-006-0206-4
  4. Mathur, T., Dutton, J. C, Base-bleed experiments with a cylindrical afterbody in supersonic flow, Journal Of Spacecraft And Rockets, 33 (1996), 1, pp. 30-37. dx.doi.org/10.2514/3.55703
  5. Andersson, K., et al., "Swedish Base Bleed" Increasing the range of artillery projectiles through base flow. Propellants, Explosives, Pyrotechnics, 1 (1976), 4, pp.69-73. dx.doi.org/10.1002/prep.19760010402
  6. Xue, X., Yu, Y., An improvement of the base bleed unit on base drag reduction and heat energy addition as well as mass addition. Applied Thermal Engineering, 109 (2016). pp. 238-250. dx.doi.org/10.1016/j.applthermaleng.2016.08.072
  7. Ding, Z., et al., Wind tunnel study of aerodynamic characteristics of base combustion. Journal of Propulsion and Power, 8 (1992), 3, pp. 630-634. dx.doi.org/10.2514/3.23525
  8. Hubbartt J E., et al., Mach 3 Hydrogen External/Base Burning. AIAA Journal, 19 (1981), 6, pp. 745-749. doi.org/10.2514/3.50998
  9. Bowman. J. E., Clayden, W. A., Cylindrical afterbodies at M sub infinity equals 2 with hot gas ejection. AIAA Journal, 6 (1968), 12, pp.2429-2431. dx.doi.org/10.2514/3.5009
  10. J. L. Herrin., Dutton, J. C., Supersonic Base Flow Experiments in the Near Wake of a Cylindrical Afterbody, AIAA Journal. 32 (1994), 1, pp. 77-83. dx.doi.org/10.2514/3.11953
  11. Przirembel, C. E., Valentine, D. T., Turbulent axisymmetric near-wake at Mach four with base injection. AIAA Journal, 8 (1970), 12, pp. 2279-2280. doi.org/10.2514/3.6104
  12. Ansys Inc., ANSYS FLUENT 17.0 licensed to MA, 2017
  13. Regodić, D. External Ballistic. (In Serbian language), Military Academy, Belgrade, Serbia, 2006.
  14. Tanner, M. Investigations into incompressible steady base flows. Aerospace Science and Technology, 14 (2010), 2, pp. 126-133. dx.doi.org/10.1016/j.ast.2009.11.007
  15. Nicolás-Pérez, F et al. On the accuracy of RANS, DES & LES turbulence models for predicting drag reduction with Base Bleed technology. Aerospace Science and Technology, 67 (2017),pp.126-140. doi.org/10.1016/j.ast.2017.03.031
  16. Novak, L., et al., Investigation of vortex shedding from an airfoil by CFD simulation and computer-aided flow visualization. Thermal Science,(2018)., pp. 1-12. doi.org/10.2298/TSCI170615002N
  17. Cvetinović, D., et al., Review of the research on the turbulence in the laboratory for thermal engineering and energy. Thermal Science, 21 (2017), Suppl. 3, pp. S875-S898. doi.org/10.2298/TSCI160221330C
  18. Orlenko, P, L. Physics of Explosion (Book in Russian language). FizMatLit, Moscow, Russia, 2002.
  19. Thunaipragasam, S., Natarajan, K. Experimental study on composite solid propellant material burning rate using matlab algorithm. Thermal Science, 20 (2016), Suppl. 4, pp. S1119-S1125. doi.org/10.2298/TSCI16S4119T
  20. Jaramaz, S., Injac, M. Method of Calculation Range of Base Bleed Projectile. (In Serbian), Military Technical Institute, Belgrade. (1989).
  21. Jaramaz, S., Injac, M. Effect of Grain Characteristics on Range of Artillery Projectiles with Base Bleed, in: First International Symposium on Special Topics in Chemical Propulsion, Hemisphere Publishing Corporation, New York, USA, ISBN 0-89116-937-7, 1991, pp. 143-157.
  22. Zhang, L., et al., Burning rate of AP/HTPB base-bleed composite propellant under free ambient pressure. Aerospace Science and Technology, 62 (2017), pp. 31-35. dx.doi.org/10.1016/j.ast.2016.12.004
  23. ***,Weibel Scientific Solvang, 2010, MFTR 2100 Medium Range TSPI & Debris Radar. Report ID CS-1017-006. Weibel Doppler Radars. Allerød Denmark. www.weibel.dk.
  24. Christopher J. F., The issue of numerical uncertainty, Applied Mathematical Modelling, 26 (2002), 2, pp.237-248. dx.doi.org/10.1016/s0307-904x(01)00058-0
  25. Regodić, D., et al., The prediction of axial aerodynamic coefficient reduction using base bleed. Aerospace Science and Technology, 31 (2013), 1, pp. 24-29. dx.doi.org/10.1016/j.ast.2013.09.001
  26. Sahu, J., et al.. Navier-Stokes Computations of Projectile Base Flow with and Without Mass Injection, AIAA Journal, 23 (1985), 9, pp. 1348-1355. dx.doi.org/10.2514/3.9091
  27. Korkegi. R. H.,Freeman . L. M., Aft-body drag reduction by combined boat-tailing and base blowing at M sub infinity equals 3. AIAA Journal, 14 (1976), 8, pp. 1143-1145. doi.org/10.2514/3.7206
  28. Tanner, M., Theoretical prediction of base pressure for steady base flow, Progress in Aerospace Sciences, 14 (1973), pp. 177-225. dx.doi.org/10.1016/0376-0421(73)90006-7