Volume 16, Issue 12 (2-2017)                   Modares Mechanical Engineering 2017, 16(12): 163-174 | Back to browse issues page

XML Persian Abstract Print


Download citation:
BibTeX | RIS | EndNote | Medlars | ProCite | Reference Manager | RefWorks
Send citation to:

Doustdar M M, Mardani M, Ghadak F. Simulation of temperature distribution for hypersonic ablative noses during flight trajectory by space marching method. Modares Mechanical Engineering 2017; 16 (12) :163-174
URL: http://mme.modares.ac.ir/article-15-8691-en.html
Abstract:   (3930 Views)
Derivation of temperature distribution, at the different sections of nose, to select the material, component, and sensitive system installation at inside of it, implicates to specifying the induced aeroheating to the nose surface. This parameter with surface temperature and recess due to surface ablation must be corrected at next time steps of flight trajectory. The different methods, to estimate or calculation of aeroheating, were created whereas the most accurate method for this purpose is numerical solution of fully navier stocks, chemical dissociation and ionization of air, mass conservation of species, turbulence modeling, combustion modeling due to surface ablation, nose heat transfer equations with time marching finite volume algorithms simultaneously. Utilizing these solvers for flight trajectory is snail, and it’s required the 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, to solve the governing equations, the space marching solvers can be used. Therefore, in this research, the 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. Therefore, the comprehensive code was created to 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.
Full-Text [PDF 792 kb]   (5123 Downloads)    
Article Type: Research Article | Subject: CFD
Received: 2016/09/23 | Accepted: 2016/10/28 | Published: 2016/12/3

Add your comments about this article : Your username or Email:
CAPTCHA

Rights and permissions
Creative Commons License This work is licensed under a Creative Commons Attribution-NonCommercial 4.0 International License.