Study on the performance of spatial discretization schemes for hypersonic flow

Abstract

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.

Numerical study on heat and drag reduction by transpiration in hypersonic flow

“…The differential scheme used in this paper has been proved to be suitable for the hypersonic flow condition (Huang and Hu, 2018). Equation (5) is discretized as follows: where Δ S I +1/2, J and boldRtrue(I,Jtrue)n are the length of side and the residual, where A and B are Jacobians matrix, boldWn=trueU¯n+1−trueU¯n, then: …”

“…The differential scheme used in this paper has been proved to be suitable for the hypersonic flow condition (Huang and Hu, 2018). Equation ( 5) is discretized as follows:…”

Flow and heat transfer analysis of laminar flow in hypersonic aircraft with variable specific heat capacity at small attack angles

“…Generally, for hypersonic flow problems, the analysis of the relevant physical parameters is mostly performed when the specific heat capacity is constant (Dong et al , 2006; Zhou et al , 2020; Giuseppe and Christian, 2022; Ding et al , 2023; Liu et al , 2023; Lee et al , 2023). However, in practice, the specific heat capacity is affected by many factors, so it is actually more suitable to be treated as a function of other variables (Anazadehsayed et al , 2017; Huang and Huang, 2017; Hu et al , 2017; Huang and Hu, 2018; Li et al , 2022; Yury et al , 2022; Yan and Zheng, 2023; Zhao et al , 2023). During flight, hypersonic aircraft will be subjected to severe aerodynamic heating, resulting in a dramatic increase in temperature, which changes the thermodynamic properties of the gas, and thus the thermal physical parameters of the air are no longer constant.…”