A Study of Spatial Discretization Schemes Applied to Cold Gas Hypersonic Flow Simulations

2005 ◽  
Author(s):  
Farney Moreira ◽  
João Azevedo
Keyword(s):  
Hypersonic Flow ◽  
Spatial Discretization ◽  
Flow Simulations ◽  
Discretization Schemes ◽  
Cold Gas

Study on the performance of spatial discretization schemes for hypersonic flow

2018 ◽  
Vol 28 (8) ◽  
pp. 1791-1808 ◽  
Author(s):  
Haiming Huang ◽  
Yumeng Hu
Keyword(s):  
Hypersonic Flow ◽  
Stokes Equations ◽  
Hypersonic Vehicles ◽  
Pressure Jump ◽  
Spatial Discretization ◽  
Finite Volume Schemes ◽  
Continuous Increase ◽  
Content Type ◽  
Near Space ◽  
Discretization Schemes

Purpose With the continuous increase of space activities and insight into space exploration, the velocity of near space hypersonic vehicles becomes higher and higher, which leads to the aerothermodynamic phenomenon getting worse around a vehicle; therefore, the exploration of numerical scheme applicability is essential for hypersonic flow simulations. Design/methodology/approach The implicit finite volume schemes are derived from axisymmetric Navier–Stokes equations for chemical equilibrium flow and programmed in Fortran. Taking the atmosphere at 30 km as an example, the performance of spatial discretization schemes such as AUSMPW and AUSMPW+ are analyzed in a range of Mach numbers from 17 to 32. Findings The AUSMPW scheme appears pressure jump near the stagnation if the Mach number is over 18, but AUSMPW+ scheme shows better performance in comparison. Originality/value This study will help the aerothermodynamic design in near space hypersonic vehicles.

On the Finite Differences Used in Reacting Flow Simulations

2015 ◽  
Vol 18 (3) ◽  
pp. 558-576
Author(s):  
Robert Prosser
Keyword(s):  
Turbulent Flows ◽  
Numerical Stability ◽  
Temperature Gradients ◽  
Finite Difference Schemes ◽  
Reacting Flow ◽  
Surprising Result ◽  
Spatial Discretization ◽  
Flow Simulations ◽  
Discretization Schemes ◽  
Effects Of Temperature

AbstractThere exist many spatial discretization schemes that are well able to provide accurate and stable approximations for isothermal turbulent flows. Comparatively little analysis has been made of the performance of these schemes in the presence of temperature gradients driven by combustion. In this paper, the effects of temperature gradients on numerical stability are explored. A surprising result is that temperature gradients in the flow have a tendency to impinge on left half plane (LHP) stability of the spatial discretization scheme. Reasons for this tendency are explored and two remedies are proposed: one based on the particular class of finite difference schemes, and one based on an alternative method of boundary condition specification.

Computational Challenges in Hypersonic Flow Simulations

2007 ◽  
Author(s):  
Seokkwan Yoon ◽  
Peter Gnoffo ◽  
Jeffery White ◽  
James Thomas
Keyword(s):  
Hypersonic Flow ◽  
Flow Simulations

A chemical equilibrium method for hypersonic flow simulations

1994 ◽  
Vol 23 (1) ◽  
pp. 143-155 ◽  
Author(s):  
Sheng-Tao Yu ◽  
Bonnie J. McBride ◽  
Kwang-Chung Hsieh ◽  
Jian-Shun Shuen
Keyword(s):  
Hypersonic Flow ◽  
Chemical Equilibrium ◽  
Flow Simulations ◽  
Equilibrium Method
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