scholarly journals Computational Study of Hypersonic Flow Past Spiked Blunt Body Using RANS and DSMC Method

2016 ◽  
Vol 25 ◽  
pp. 892-899 ◽  
Author(s):  
Jiss J. Sebastian ◽  
Sandeep Eldho James ◽  
Abhilash Suryan
Keyword(s):  
Hypersonic Flow ◽  
Blunt Body ◽  
Computational Study ◽  
Dsmc Method ◽  
Flow Past

Hypersonic flow past a spherically blunted nose cone: a computational study

2020 ◽  
Vol 20 (2) ◽  
pp. 105
Author(s):  
Ashish Narayan ◽  
S. Narayanan ◽  
Rakesh Kumar ◽  
Chintoo Sudhiesh Kumar ◽  
Gopalan Jagadeesh
Keyword(s):  
Hypersonic Flow ◽  
Computational Study ◽  
Flow Past ◽  
Nose Cone

Hypersonic flow past a spherically blunted nose cone: A computational study

2019 ◽  
Vol 1 (1) ◽  
pp. 1
Author(s):  
Jagadeesh Gopalan ◽  
Chintoo Kumar ◽  
Rakesh Kumar ◽  
S. Narayanan ◽  
Ashish Narayan
Keyword(s):  
Hypersonic Flow ◽  
Computational Study ◽  
Flow Past ◽  
Nose Cone

Numerical simulation of a hypersonic flow past a blunt body

2017 ◽  
Vol 27 (6) ◽  
pp. 1351-1364 ◽  
Author(s):  
Yumeng Hu ◽  
Haiming Huang ◽  
Zimao Zhang
Keyword(s):  
Hypersonic Flow ◽  
Blunt Body ◽  
Stokes Equations ◽  
Thermal Protection ◽  
Gas Temperature ◽  
Perfect Gas ◽  
Viscous Effects ◽  
Finite Volume Schemes ◽  
Content Type ◽  
Flow Past

Purpose The purpose of this paper is to explore the characteristics of hypersonic flow past a blunt body. Design/methodology/approach The implicit finite volume schemes are derived from axisymmetric Navier–Stokes equations by means of AUSM+ and LU-SGS methods, and programmed in FORTRAN. Based on the verified result that a 2D axisymmetric chemical equilibrium flow has a good agreement with the literature, the characteristics of hypersonic flow past a sphere are simulated by using four different models which involve four factors, namely, viscous, inviscid, equilibrium and calorically perfect gas. Findings Compared with the calorically perfect gas under hypervelocity condition, the shock wave of the equilibrium gas is more close to the blunt body, gas density and pressure become bigger, but gas temperature is lower due to the effect of real gas. Viscous effects are not obvious in the calculations of the equilibrium gas or the calorically perfect gas. In a word, the model of equilibrium gas is more suitable for hypersonic flow and the calculation of viscous flow has a smaller error. Originality/value The computer codes are developed to simulate the characteristics of hypersonic flows, and this study will be helpful for the design of the thermal protection system in hypersonic vehicles.

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