Numerical investigation of a chemically reacting and rarefied hypersonic flow field

Gijare, Harshal; Bhagat, Apurva; Dongari, Nishanth

doi:10.1007/s00193-018-0882-5

Cited by 4 publications

(4 citation statements)

References 20 publications

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“…Note that even triatomic molecules are difficult to deal with at high temperatures, and the correction factor method is proposed. , To justify interest in the NH molecule at very high temperatures, it can be reminded that this radical can be created in ammonia shock heated to 2900–9600 K . High temperature heat capacities are also of interest in the research of laser ignition models and hypersonic flows . Dynamical studies of the NH molecule at high temperatures are of interest in astrophysics …”

Section: Introductionmentioning

confidence: 99%

“…18,19 To justify interest in the NH molecule at very high temperatures, it can be reminded that this radical can be created in ammonia shock heated to 2900−9600 K. 20 High temperature heat capacities are also of interest in the research of laser ignition models 21 and hypersonic flows. 22 Dynamical studies of the NH molecule at high temperatures are of interest in astrophysics. 23 The present approach is the simplest solution of the problem of high temperature thermodynamics of diatomic molecules if the ground and excited energy curves of high quality are available and scattering states can be neglected.…”

Section: Introductionmentioning

confidence: 99%

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Uncertainty of High Temperature Heat Capacities: The Case Study of the NH Radical

Buchowiecki

2021

J. Phys. Chem. A

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The difficulties in calculation of high temperature heat capacities and discrepancies between available data are discussed in the case of the NH molecule. The source of those inaccuracies are the underlining potential energy curves. The relevant partition functions and heat capacities are calculated with the classical Wigner–Kirkwood corrected method. In addition to the ground electronic state, also four excited states are taken into account. Two potential energy curves and experimental energy levels of the ground state are considered.

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Section: Introductionmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Uncertainty of High Temperature Heat Capacities: The Case Study of the NH Radical

Buchowiecki

2021

J. Phys. Chem. A

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“…The authors have earlier validated the developed code for various standard test cases such as: (i) Flow over a blunt conical object: 51 heat load and pressure data on the surface of a blunt conical object in hypersonic flow regime (Ma ¼ 10) is validated against experimental data. (ii) Flow over a sphere: 52 Sonic under-expanded jet in quiescent ambient conditions: 53 density in the flow field, location, and diameter of a Mach disk for a helium jet expanding in the air atmosphere, is validated against experimental data and analytical relations.…”

Section: Solver Validationmentioning

confidence: 99%

Modeling of a reaction control jet interacting with high-speed cross-flow in slip flow regime

Bhagat

Gijare

Dongari

2019

Proceedings of the Institution of Mechanical Engineers, Part G:

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Numerical investigation of a sonic reaction control jet interacting with the high-speed cross-flow has been carried out over a generic missile body. Simulations are performed in the early-hypersonic slip flow regime for air, CO2, and helium jet gases. An open source computational fluid dynamics tool, OpenFOAM is used to model the steady state, three-dimensional compressible Navier–Stokes equations with k-ω shear stress transport turbulence model. The conventional computational fluid dynamics solver is extended with additional features, such as transport of species, nonequilibrium boundary conditions for velocity slip and temperature jump, and a heat load calculation utility based on the sliding friction effect. The extended solver is validated with the direct simulation Monte Carlo results for the case of a sonic argon jet injected into hypersonic nitrogen cross-flow. The extended solver is able to accurately capture all the qualitative flow features like separation shock, bow shock, and barrel shock, and it also improves heat load predictions in the slip flow regime. The main objective of the present work is to study the effect of rarefaction and change in jet gas species on the complex flow topology, heat load distribution, and spread of jet gas on the missile body. Heat load predictions are found to be strongly dependent on the slip velocity of molecules in addition to the temperature gradient near the wall. The strength of a bow shock and a barrel shock is higher for helium jet, compared to air and CO2 jets, which spread more along the missile body, and weaker shocks and reduced heat load is generated. The current work is significant from the perspective of the thermal design of spacecraft surfaces and positioning of the optical sensors.

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“…However, many issues still remain open concerning accurate simulations of the heat transfer rate for hypersonic vehicles. Numerical calculation results of aeroheating relies on many factors, such as numerical schemes, physical models, freestream conditions, catalytic conditions, transport property, grid scale and so on [1][2][3][4][5].…”

Section: Introductionmentioning

confidence: 99%

Grid convergence and influence of wall temperature in the calculation of thermochemical non-equilibrium heat flux

Luo

Liu

2020

J. Phys. D: Appl. Phys.

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In order to accurately simulate the aerothermal environment of hypersonic vehicles, research on the grid convergence and influence of wall temperature is conducted in this paper. Two kinds of gas models are utilized for numerical simulations, namely the thermochemical non-equilibrium gas model and the perfect gas model. A typical hypersonic vehicle-the Orbital Reentry Experiment capsule-is used as the simulation object. After designing a series of coarse and refined grids, numerical simulations are conducted with the two gas models under different wall temperatures. Results indicate that the heat transfer prediction is very sensitive to normal grid spacing at the wall. Grid convergence for the two gas models is basically the same. When the grid is convergent in the hypersonic flow heat flux calculation, the required normal height of the first layer is smaller for the low wall temperature condition, compared with the high wall temperature case. Moreover, when the grid-convergence requirement is met, the heat flux increases with the reduction of wall temperature for all of the simulated flight conditions.

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Numerical investigation of a chemically reacting and rarefied hypersonic flow field

Cited by 4 publications

References 20 publications

Uncertainty of High Temperature Heat Capacities: The Case Study of the NH Radical

Uncertainty of High Temperature Heat Capacities: The Case Study of the NH Radical

Modeling of a reaction control jet interacting with high-speed cross-flow in slip flow regime

Grid convergence and influence of wall temperature in the calculation of thermochemical non-equilibrium heat flux

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