Calculation of viscous hypersonic shock layer with mass injection for moderately small reynolds numbers

Ankudinov, A. L.

doi:10.1007/bf01019272

Cited by 3 publications

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“…The effect of injecting gaseous coolants on heat transfer in hypersonic perfect gas flow near blunt bodies was studied by Gershbein and Kolesnikov 13 and Emelianova and Pavlov 14 on the basis of the complete system of Navier-Stokes equations, and by Moss 12 , Shen et al 15 , Ankundinov 16 , Provotorov and Stepanov 17,18 , and Botin 19 on the basis of the thin viscous shock layer model developed by Cheng 2 . Provotorov and Stepanov 17,18 had found universal relations between the relative heat flux and the generalized blowing parameters.…”

Section: Introductionmentioning

confidence: 99%

Heat Transfer on a Hypersonic Sphere with Diffuse Rarefied-Gas Injection

Riabov

2004

42nd AIAA Aerospace Sciences Meeting and Exhibit

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The interaction of a diffusing outgas flow from a sphere nose opposing a hypersonic free stream is studied numerically by the direct simulation Monte-Carlo technique under the transitional rarefied-gas-flow regime conditions at Knudsen numbers from 0.016 to 1.5 and blowing factors from 0.15 to 1.5. Strong influences of the blowing factor (the ratio of outgas mass flux to upstream mass flux) and the Knudsen number on the flow structure about a sphere (temperature fields, the configuration of mixing flow zones) and on heat distributions along the spherical surface have been found. At large blowing factors, the injected gas significantly reduces heat flux in wide area near the spherical nose. This effect is more pronounced for light gas (helium) injection in the near-continuum flow. Nomenclature d = orifice diameter, 0.002 m f = mole fraction of helium G w = mass injection rate ratio ("blowing" factor) Kn ∞,R = Knudsen number M = Mach number p = pressure, N/m 2 R = sphere radius, 0.015 m Re 0,R = Reynolds number St = Stanton number s = coordinate along a spherical surface T = temperature t w = temperature factor, T w /T 0 x = coordinate along an axis of body symmetry subscripts R = sphere radius as a length-scale parameter w = wall condition 0 = stagnation flow condition ∞ = freestream parameter

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Section: Introductionmentioning

confidence: 99%

Heat Transfer on a Hypersonic Sphere with Diffuse Rarefied-Gas Injection

Riabov

2004

42nd AIAA Aerospace Sciences Meeting and Exhibit

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“…10 on the basis of the complete system of Navier-Stokes equations, and in Ref. 9,11,12 on the basis of the thin viscous shock layer model [3]. Heat transfer in the presence of hydrogen blowing and combustion was studied in Ref.…”

Section: Introductionmentioning

confidence: 99%

Numerical Studies of Heat Transfer on Hypersonic Blunt Bodies with Gas Injection

Riabov¹

Proceedings of the Seventh International Conference on Engineering Computational Technology

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Numerical analysis of the gas flow in the thin viscous shock layers (TVSL) is presented under conditions of intensive gas blowing from the blunt body surface for various injection factors under the continuum and rarefied conditions. Nonequilibrium parameters in the multicomponent TVSL were evaluated for slot and uniform injections of air, helium, and hydrogen. Numerical results indicate that the most effective cooling of the probe surface occurs at moderate uniform injections and moderate Reynolds numbers.

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Mathematical model of a kinetic boundary layer

Ankudinov

2014

Comput. Math. and Math. Phys.

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Calculation of viscous hypersonic shock layer with mass injection for moderately small reynolds numbers

Cited by 3 publications

References 0 publications

Heat Transfer on a Hypersonic Sphere with Diffuse Rarefied-Gas Injection

Heat Transfer on a Hypersonic Sphere with Diffuse Rarefied-Gas Injection

Numerical Studies of Heat Transfer on Hypersonic Blunt Bodies with Gas Injection

Mathematical model of a kinetic boundary layer

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