Axisymmetric hypersonic jet interaction. II - A combined experimental and computational study

Gilmore, Martin R.; Warburton, Katarzyna

doi:10.2514/6.1995-414

Cited by 6 publications

(2 citation statements)

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“…To validate the numerical techniques, comparisons with results from available low density experimental studies must be made. Several experimental and computational jet interaction studies relevant to RCS interactions in the rarefied regime have been accomplished recently for flow in low density perfect gas environments for simple geometries [6][7][8][9][10] . However, more of these jet interaction comparisons are required to gain greater confidence in the capability of existing numerical techniques and to set limits of technique applicability for studies of RCS interactions for RLV entry, planetary aerobraking, and other missions in the rarefied flow regime.…”

Section: Problem Descriptionmentioning

confidence: 99%

Numerical study of a continuum sonic jet interacting with a rarefied flow

Glass

1997

32nd Thermophysics Conference

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Section: Problem Descriptionmentioning

confidence: 99%

Numerical study of a continuum sonic jet interacting with a rarefied flow

Glass

1997

32nd Thermophysics Conference

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“…Few researchers 3,20,21 have also explored the direct simulation Monte Carlo i.e. direct simulation Monte Carlo (DSMC) and CFD hybrid approach to compute the jet-cross-flow interaction in the altitude range of 90-150 km i.e.…”

Section: Introductionmentioning

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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