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Abstract
Due to sever aerodynamic heating, the protection of forebody of scramjet is crucial for hypersonic flight. In present work, a new cooling system is proposed and investigated for the protection of nose cone at hypersonic flight. Computational fluid dynamic is used for the simulation of the lateral and axial coolant jet released from the spike at high-velocity condition. The primary goal is to find optimum jet location for efficient cooling of nose and spike assembly. Influence of two coolant jets (Carbon dioxide and Helium) on the mechanism of cooling system are fully investigated. For simulation, RANS equations are coupled with species transport equation and SST turbulence model. Two different jet configurations (axial disk positions) are investigated to obtain efficient condition for protection of nose cone at hypersonic flight. Our results indicate that the presence of the spike on the nose cone decreases pressure up to 33% on the main body and the shifts the maximum pressure to higher angles because of the deflection of the air stream. Maximum pressure drops about 50% by injection of the coolant disk jet (C2) at angle of 55 deg.
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Details
1 K.N. Toosi University of Technology, Faculty of Civil Engineering, Tehran, Iran (GRID:grid.411976.c) (ISNI:0000 0004 0369 2065)
2 Cihan University-Erbil, Department of Civil Engineering, College of Engineering, Erbil, Iraq (GRID:grid.472236.6) (ISNI:0000 0004 1784 8702)
3 Babol Noshirvani University of Technology, Department of Mechanical Engineering, Babol, Iran (GRID:grid.411496.f) (ISNI:0000 0004 0382 4574)
4 Institute of Infrastructure Technology Research and Management (IITRAM), Department of Mechanical & Aerospace Engineering, Ahmedabad, India (GRID:grid.494529.7) (ISNI:0000 0004 4684 9034)