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Paper Information

Journal:   MODARES MECHANICAL ENGINEERING   MARCH 2017 , Volume 16 , Number 12 ; Page(s) 163 To 174.
 
Paper: 

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

 
 
Author(s):  DOUSTAR MOHAMMAD MEHDI*, MARDANI MORTEZA, GHADAK FARHAD
 
* DEPARTMENT OF MECHANICAL AND AEROSPACE ENGINEERING, IMAM HUSSEIN UNIVERSITY, TEHRAN, IRAN
 
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.

 
Keyword(s): TEMPERATURE CONTOUR, SPACE MARCHING SOLVERS, VISCOUS SHOCK LAYER METHOD, SIMILARITY OF VISCOUS BOUNDARY LAYER METHOD, SURFACE ABLATION
 
 
References: 
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Citations: 
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+ Click to Cite.
APA: Copy

DOUSTAR, M., & MARDANI, M., & GHADAK, F. (2017). SIMULATION OF TEMPERATURE DISTRIBUTION FOR HYPERSONIC ABLATIVE NOSES DURING FLIGHT TRAJECTORY BY SPACE MARCHING METHOD. MODARES MECHANICAL ENGINEERING, 16(12 ), 163-174. https://www.sid.ir/en/journal/ViewPaper.aspx?id=572537



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. 2017 [cited 2021July31];16(12 ):163-174. Available from: https://www.sid.ir/en/journal/ViewPaper.aspx?id=572537



IEEE: Copy

DOUSTAR, M., MARDANI, M., GHADAK, F., 2017. SIMULATION OF TEMPERATURE DISTRIBUTION FOR HYPERSONIC ABLATIVE NOSES DURING FLIGHT TRAJECTORY BY SPACE MARCHING METHOD. MODARES MECHANICAL ENGINEERING, [online] 16(12 ), pp.163-174. Available: https://www.sid.ir/en/journal/ViewPaper.aspx?id=572537.



 
 
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