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Paper Information

Journal:   AMIRKABIR   SPRING 2003 , Volume 14 , Number 54-B; Page(s) 445 To 462.
 
Paper: 

Calculation Of Graphite Ablation Rate Near The Missiles Nosetip Stagnation Point

 
 
Author(s):  Mazaheri K., Soury H.
 
* 
 
Abstract: 
A method is presented for prediction of graphite ablation rate at the stagnation region of an axisymmetric blunted nosetip of hypersonic vehicles. For this purpose, governing equations of reacting boundary layer are derived with appropriate boundary conditions. Frozen gas phase with surface reaction is postulated. This assumption on the graphite grade, is reliable at temperature about 2750 to 4450 K. ermochemical equilibrium he graphite surface between CO2, CO, and O2 is assumed. The governing equations are solved by a self-similar method. The comparison of the self-similar solution with experimental data, indicates a good agreement.
 
Keyword(s): ABLATION ,GRAPHITE, HYPERSONIC, HEATING, AERODYNAMIC
 
 
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APA: Copy

MAZAHERI, K., & SOURY, H. (2003). CALCULATION OF GRAPHITE ABLATION RATE NEAR THE MISSILES NOSETIP STAGNATION POINT. AMIRKABIR, 14(54-B), 445-462. https://www.sid.ir/en/journal/ViewPaper.aspx?id=738



Vancouver: Copy

MAZAHERI K., SOURY H.. CALCULATION OF GRAPHITE ABLATION RATE NEAR THE MISSILES NOSETIP STAGNATION POINT. AMIRKABIR. 2003 [cited 2022January19];14(54-B):445-462. Available from: https://www.sid.ir/en/journal/ViewPaper.aspx?id=738



IEEE: Copy

MAZAHERI, K., SOURY, H., 2003. CALCULATION OF GRAPHITE ABLATION RATE NEAR THE MISSILES NOSETIP STAGNATION POINT. AMIRKABIR, [online] 14(54-B), pp.445-462. Available: https://www.sid.ir/en/journal/ViewPaper.aspx?id=738.



 
 
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