SIMULATION OF TEMPERATURE DISTRIBUTION FOR HYPERSONIC ABLATIVE NOSES DURING FLIGHT TRAJECTORY BY SPACE MARCHING METHOD

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DOUSTAR MOHAMMAD MEHDI; MARDANI MORTEZA; GHADAK FARHAD

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Journal: Modares Mechanical Engineering Year:2017 | Volume:16 | Issue:12 Page(s): 163-174

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Title

SIMULATION OF TEMPERATURE DISTRIBUTION FOR HYPERSONIC ABLATIVE NOSES DURING FLIGHT TRAJECTORY BY SPACE MARCHING METHOD

Author(s)

DOUSTAR MOHAMMAD MEHDI | MARDANI MORTEZA | GHADAK FARHAD | Issue Writer Certificate

Keywords

TEMPERATURE CONTOURQ1

SPACE MARCHING SOLVERSQ1

VISCOUS SHOCK LAYER METHODQ1

SIMILARITY OF VISCOUS BOUNDARY LAYER METHODQ1

SURFACE ABLATIONQ1

Abstract

Derivation of temperature distribution at the different sections of nose in order to select the material, component, and sensitive system installation on the inside of it involves specifying the induced aeroheating to nose surface. This parameter with surface temperature and recess due to SURFACE ABLATION must be corrected at the next time step of flight trajectory. Different methods to estimate or calculate aeroheating were created, however, the most accurate method for this purpose is numerical solution of fully Navier Stokes, chemical dissociation and ionization of air, mass conservation of species, turbulence modeling, combustion modeling due to SURFACE ABLATION, and nose heat transfer equations with time marching finite volume algorithms simultaneously. Utilizing these solvers for flight trajectory is frivoling, and requires high computational memory. Therefore, the finite difference method is used and the governing equations are translated to curvature coordinate by mapping terms. By using this translation, the SPACE MARCHING SOLVERS can be used to solve the governing equations. Therefore, in this research, a more accurate estimation of temperature distribution for 3-D nose of supersonic and hypersonic vehicles was presented by using the numerical SPACE MARCHING SOLVERS such as viscous shock layers and viscous boundary layer methods. So the comprehensive code was created for this purpose.The results of this code were validated by using the temperature telemetry results of flight tests. The relative error of the results was less than 10 percent.

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APA: Copy

DOUSTAR, MOHAMMAD MEHDI, MARDANI, MORTEZA, & GHADAK, FARHAD. (2017). SIMULATION OF TEMPERATURE DISTRIBUTION FOR HYPERSONIC ABLATIVE NOSES DURING FLIGHT TRAJECTORY BY SPACE MARCHING METHOD. MODARES MECHANICAL ENGINEERING, 16(12 ), 163-174. SID. https://sid.ir/paper/178169/en

Vancouver: Copy

DOUSTAR MOHAMMAD MEHDI, MARDANI MORTEZA, GHADAK FARHAD. SIMULATION OF TEMPERATURE DISTRIBUTION FOR HYPERSONIC ABLATIVE NOSES DURING FLIGHT TRAJECTORY BY SPACE MARCHING METHOD. MODARES MECHANICAL ENGINEERING[Internet]. 2017;16(12 ):163-174. Available from: https://sid.ir/paper/178169/en

IEEE: Copy

MOHAMMAD MEHDI DOUSTAR, MORTEZA MARDANI, and FARHAD GHADAK, “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, 2017, [Online]. Available: https://sid.ir/paper/178169/en

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