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

Glass, Christopher E.

doi:10.2514/6.1997-2536

Cited by 15 publications

(4 citation statements)

References 11 publications

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“…Glass et al 26 performed a numerical study for a flow based on an experiment of a continuum sonic jet interacting with a hypersonic rarefied flow about a sharp leading edge flat plate. They presented CFD (GASP code) and an uncoupled CFD-DSMC solution for the case of a sonic argon jet interacting with the rarefied nitrogen freestream.…”

Section: Solver Validationmentioning

confidence: 99%

“…Heat load values are calculated based on the slip velocity and shear stress in addition to conventional Fourier law of heat conduction, and species transport equations are solved. The solver is validated for the shock wave interaction and heat load data with DSMC, 26 and against experimental wind tunnel data of pressure coefficient values. 5 The major objective of present work is to study the effect of rarefaction and change in jet gas species on the complex flow topology, associated localized heat load distribution and spread of jet gas on missile body.…”

Section: Introductionmentioning

confidence: 99%

“…Comparison of flow-field streamlines on the symmetry plane: (a) DSMC solution with C-CFD (CFD-GASP) solution26 and, (b) DSMC solution26 with E-CFD solution. All the flow features are qualitatively captured in the E-CFD solution.…”

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confidence: 99%

“…Schematic of a flat plate model. Sonic argon jet interacts with the high-speed rarefied nitrogen cross-flow 26. …”

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confidence: 99%

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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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Section: Solver Validationmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

mentioning

confidence: 99%

“…Schematic of a flat plate model. Sonic argon jet interacts with the high-speed rarefied nitrogen cross-flow 26. …”

mentioning

confidence: 99%

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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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Application highlights of the DSMC Analysis Code (DAC) software for simulating rarefied flows

LeBeau

Lumpkin

2001

Computer Methods in Applied Mechanics and Engineering

110

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Planar Laser-Induced Iodine Fluorescence Measurements in Rarefied Hypersonic Flow

Cecil

McDaniel²

2005

AIP Conference Proceedings

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Abstract.A planar laser-induced fluorescence (PLIF) technique is discussed and applied to measurement of time-averaged values of velocity and temperature in an I,-seeded N, hypersonic free jet facility. Using this technique, a low temperature, non-reacting, hypersonic flow over a simplified model of a reaction control system (RCS) was investigated. Data are presented of rarefied Mach 12 flow over a sharp leading edge flat plate at zero incidence, both with and without an interacting jet issuing from a nozzle built into the plate. The velocity profile in the boundary layer on the plate was resolved. The slip velocity along the plate, extrapolated from the velocity profile data, varied from nearly 100% down to 10% of the freestream value. These measurements are compared with results of a DSMC solution. The velocity variation along the centerline of a jet issuing from the plate was measured and found to match closely with the correlation of Ashkenas and Sherman. The velocity variation in the oblique shock terminating the jet was resolved sufficiently to measure the shock wave thickness. IODINE FLUORESCENCE MEASUREMENT TECHNIQUENumerous methods have been reported in the literature for measurement of thermodynamic properties in supersonic flows using laser-induced fluorescence. This paper presents results of a technique based on narrowband excitation of fluorescence from nuclear hyperfine components in the BHX electronic transition of molecular iodine. This approach was developed to study low temperature flows of I,-seeded N, gas. A tunable single frequency laser beam is expanded and collimated into a thin sheet and passed into a low density wind tunnel flow, causing I, molecules to fluoresce within a selected planar section of the flow-field. A series of images are taken of the fluorescence with a charge-coupled device (CCD) array as the laser frequency is incrementally tuned over selected lines in the I, absorption spectrum. The fluorescence signal versus frequency is thereby obtained for any point in the plane of the laser sheet, within the resolution of the digital image. These absorption spectra can provide information on the local thermodynamic conditions in the flow. This paper describes PLIF measurements of velocity and temperature made in a low density, low temperature, hypersonic flow over a simplified model of an RCS [ 11, intended to support assessment of a hybrid numerical solution method for such flows described in [2,3].The fluorescence signal produced by I, vapor (in a stationary, low pressure carrier gas) from a single transition line i, centered at frequency v~,~, due to excitation at frequency v, is given by [ 1,4] where C is a constant representing signal collection efficiency and molecular constants, I is excitation source intensity, n is I, number density, P is carrier gas pressure, T is temperature, f,,,l,ll is the Boltzmann population of the ground vibrational-rotational state v" J", q,,#l is the Franck-Condon factor, g, , is the hyperfine degeneracy, Shf,i is the hyperfine line strength, S...

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

Cited by 15 publications

References 11 publications

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

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

Application highlights of the DSMC Analysis Code (DAC) software for simulating rarefied flows

Planar Laser-Induced Iodine Fluorescence Measurements in Rarefied Hypersonic Flow

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