Numerical simulation of a hypersonic flow past a blunt body

Hu, Yumeng; Huang, Haiming; Zhang, Zimao

doi:10.1108/hff-05-2016-0187

Cited by 11 publications

(3 citation statements)

References 18 publications

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“…To achieve this, the expected aerothermal heating for the entire reentry trajectory should be predicted a priori. Fay and Riddell (1958) proposed an empirical formula for estimating the stagnation-point heat flux on the surface of a blunt body in hypersonic flows (Hu et al, 2017;Tchuen et al, 2005). Fay and Riddell (F-R) established nonlinear ordinary differential equations at the stagnation point and obtained an explicit formula for the stagnation-point heat flux.…”

Section: Evaluation Ofmentioning

confidence: 99%

Evaluation of Fay and Riddell formula under hypersonic flight conditions

Lee

Yang

Kim

2022

HFF

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Purpose The Fay and Riddell (F–R) formula is an empirical equation for estimating the stagnation-point heat flux on noncatalytic and fully catalytic surfaces, based on an assumption of equilibrium. Because of its simplicity, the F–R has been used extensively for reentry flight design as well as ground test facility applications. This study aims to investigate the uncertainties of the F-R formula by considering velocity gradient, chemical species at the boundary layer edge, and the thermochemical nonequilibrium (NEQ) behind the shock layer under various hypersonic NEQ flow environments. Design/methodology/approach The stagnation-point heat flux calculated with the F–R formula was evaluated by comparison with thermochemical NEQ calculations and existing flight experimental values. Findings The comparisons showed that the F–R underestimated the noncatalytic heat flux, because of the chemical composition at the surface. However, for fully catalytic heat flux, the F–R results were similar to values of surface heat flux from thermochemical NEQ calculations, because the F–R formula overestimates the diffusive heat flux. When compared with the surface heat flux results obtained from flight experimental data, the F–R overestimated the fully catalytic heat flux. The error was 50% at most. Originality/value The results provided guidelines for the F–R calculations under hypersonic flight conditions and for determining the approximate error range for noncatalytic and fully catalytic surfaces.

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Section: Evaluation Ofmentioning

confidence: 99%

Evaluation of Fay and Riddell formula under hypersonic flight conditions

Lee

Yang

Kim

2022

HFF

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“…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.…”

Section: Introductionmentioning

confidence: 99%

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

Du,

Wang,

Zhang

et al. 2023

HFF

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Purpose As to different angles of attack and nonlinear problems caused by high temperatures in coexisting hypersonic aircraft, people mainly rely on fluid software for research but lack analysis of flow mechanisms. Owing to computational difficulties, few people use numerical algorithms to combine them for discussion. Hence, this study aims to make a deep inquiry into the laminar flow and heat transfer of compressible Newtonian fluid in hypersonic aircraft with small attack angles. Design/methodology/approach In this paper, on the basis of mass, momentum and energy conservation laws, the governing equations of the hypersonic boundary layer are established. Viscosity, specific heat capacity and thermal conductivity are considered nonlinear functions concerning temperature. In virtue of the MacCormack finite difference method, the stationary numerical solutions are solved directly, and the validity of the algorithm is verified. Findings The results demonstrate that at Mach number 5, compared to the 0° attack angle, the maximum temperature near-wall at the 3° attack angle increases by about 25%. An enjoyable phenomenon is discovered, where the position corresponding to the maximum wall shear force shifts back as the attack angle and Mach number increase. The relationship between the near-wall maximum temperature versus attack angle and Mach number is fitted through numerical calculation results. Originality/value Empirical formulas can be used to estimate heat transfer characteristics at small attack angles, which will guide the design of aircraft thermal protection systems.

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“…Although many near space hypersonic vehicles, such as X-37 (Gülhan et al, 2014), X-51 (Schimisseur, 2015) and Falcon HTVs (Walker et al, 2008), have been succeeded in their missions, the exploration of aerothermodynamic problems is the principle obstacle because the velocities and altitudes at which these vehicles would operate are different, and sometimes more severe (Huang and Huang, 2015;Hu et al, 2016aHu et al, , 2016bLi et al, 2016), than those went through in the past. As future hypersonic vehicle quests to fly higher and faster, the environment surrounding the vehicle could be more dramatically changed (Hu et al, 2016a(Hu et al, , 2016bCai 2016;Yuan et al, 2017) and more difficult to simulate in ground-based test facilities (Doig et al, 2016), which makes the numerical simulations become increasingly important issues (Park et al, 2016;Boyd et al, 2010). Whether the existing numerical methods can apply to higher velocity is an urgent problem to be solved.…”

Section: Introductionmentioning

confidence: 99%

Study on the performance of spatial discretization schemes for hypersonic flow

Huang

2018

HFF

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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.

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Numerical simulation of a hypersonic flow past a blunt body

Cited by 11 publications

References 18 publications

Evaluation of Fay and Riddell formula under hypersonic flight conditions

Evaluation of Fay and Riddell formula under hypersonic flight conditions

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

Study on the performance of spatial discretization schemes for hypersonic flow

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