A grid strategy for predicting the space plane's hypersonic aerodynamic heating loads

Qu, Feng; Chen, Jiaojiao; Sun, Daoyuan; Bai, Junqiang; Zuo, Guang

doi:10.1016/j.ast.2019.01.049

Cited by 56 publications

(15 citation statements)

References 22 publications

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“…Subsequently, the turbulence gradually dissipated as the mesh approached the free stream condition, which was expected. Therefore, the values of y + and N were sufficient, so we could calculate the maximum growth ratio r by Equation (14). The first layer height y H and the maximum growth ratio were (1.49 × 10 −6 , 1.42), (1.38 × 10 −6 , 1.42) and (8.42 × 10 −6 , 1.34) respectively.…”

Section: Grid Strategymentioning

confidence: 99%

“…[13] reveals that the aspect ratio of wall cells near the shock is a major factor and Ref. [14] suggests that the aspect ratio of wall cells near the shock should be larger than six for predicting hypersonic heating, taking a blunt body and a blunt cone as examples. The experimental data of X33, which is a reusable reentry hypersonic vehicle, are used to validate the above conclusions.…”

Section: Introductionmentioning

confidence: 99%

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An Effective Simulation Scheme for Predicting the Aerodynamic Heat of a Scramjet-Propelled Vehicle

Zhang

2021

Applied Sciences

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Currently, aerothermal research into scramjet-propelled vehicles characterized by a wedge-shaped section is relatively sparse. Based on the Mach number, grid strategy, and numerical method, an effective simulation scheme for predicting the aerodynamic heat of a scramjet-propelled vehicle during flight is proposed in this paper. At different Mach numbers, the appropriate grid strategy and numerical method were determined by validation tests. Two-dimensional external flow field models based on wedge sections were established and, unlike in blunt bodies, the tests showed that at the high supersonic stage, the ideal cell Reynolds number should be no larger than 16. At the hypersonic stage, the ideal cell Reynolds number and aspect ratio of wall cells near the shock should be no larger than 40, and the AUSM+ flux type performs better than Roe’s FDS flux type at the above stages. The aerothermal prediction indicates that during a flight time of about 34 s, the temperature change reaches about 1913.35 °C, and the maximum average temperature change rate reaches 115 °C/s.

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Section: Grid Strategymentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

An Effective Simulation Scheme for Predicting the Aerodynamic Heat of a Scramjet-Propelled Vehicle

Zhang

2021

Applied Sciences

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“…According to Ref. [16,18,31], the number of grids and the height of the first layer play a significant role in the accuracy of simulation results and even determine whether they can converge. For this reason, the structured grid is divided in this paper.…”

Section: Resultsmentioning

confidence: 99%

“…Ref. [17,18] showed that a cell Reynolds number of about 20 in the first grid layer was reasonable. It is found that the heat flux converges when the wall cell Reynolds number is less than or equal to 3 [19].…”

Section: Introductionmentioning

confidence: 99%

CFD Simulation Strategy for Hypersonic Aerodynamic Heating around a Blunt Biconic

Chen

2021

International Journal of Aerospace Engineering

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The design of the thermal protection system requires high-precision and high-reliability CFD simulation for validation. To accurately predict the hypersonic aerodynamic heating, an overall simulation strategy based on mutual selection is proposed. Foremost, the grid criterion based on the wall cell Reynolds number is developed. Subsequently, the dependence of the turbulence model and the discretization scheme is considered. It is suggested that the appropriate value of wall cell Reynolds number is 1 through careful comparison between one another and with the available experimental data. The excessive number of cells is not recommended due to time-consuming computation. It can be seen from the results that the combination of the AUSM+ discretization scheme and the Spalart-Allmaras turbulence model has the highest accuracy. In this work, the heat flux error of the stagnation point is within 1%, and the overall average relative error is within 10%.

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“…The advent of hypersonic vehicle has created hope in this closure of gap and hence a lot of research is conducted in this area. Various researchers [1][2][3][4][5][6][7][8][9][10] have investigated shock wave boundary layer and interaction physics through design modifications such as blunting, cavitation, ramping, flaring, external attachments such as aero disc or spike etc. to evaluate and understand the importance of these design features and also to measure the dependency on these features.…”

Section: Introductionmentioning

confidence: 99%

Hypersonic Flows Over Multi-Ramp Configurations

Sundarraj¹,

Güven²,

Kulkarni³

et al. 2019

IJRTE

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The effects of attaching multiple ramps to the standard double ramp configuration along with variations in ramp angle, free-stream Mach number and surface temperature are discussed in this investigation. This study investigates the changes associated with shock wave boundary layer interaction (SWBLI) due to ramp induced flow breakdown and the flow field fluctuation with changes in flow characteristics and design. This type of ramp junctions typically features in re-entry vehicles, engine intakes, system and sub-system junctions, control surfaces, etc. Ramp junctions usually are associated with strong separation bubble that has significant upstream influence impacting the effectiveness of aerodynamic surfaces, engine performance, thermal behavior and stability. Computation studies are carried out using Second order accurate, finite volume RANS solver considering compressible laminar flow characteristics, with solver settings provided like experimental conditions as per literature. Comprehensive double ramp studies with suggestions on reducing the separation bubble size are invariantly considered in literature, however there has been no study in understanding the inclusion of additional ramps in such flow scenarios. At the end of this study it was evident that such complex junction needs detailed understanding on how they benefit or impact the overall design of the system. It also gave a very good insight on the nature of flow around such complex junctions and instills motivation for detailed experimental understanding.

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A grid strategy for predicting the space plane's hypersonic aerodynamic heating loads

Cited by 56 publications

References 22 publications

An Effective Simulation Scheme for Predicting the Aerodynamic Heat of a Scramjet-Propelled Vehicle

An Effective Simulation Scheme for Predicting the Aerodynamic Heat of a Scramjet-Propelled Vehicle

CFD Simulation Strategy for Hypersonic Aerodynamic Heating around a Blunt Biconic

Hypersonic Flows Over Multi-Ramp Configurations

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