Film-Cooling Effectiveness and Skin Friction in Hypersonic Turbulent Flow

Cary, A. M.; Hefner, J. N.

doi:10.2514/3.50348

Cited by 78 publications

(13 citation statements)

References 5 publications

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“…It is known that injection of gas into a boundary layer can be effective in reducing heat transfer rates and skin friction 17 . This process is often referred to as film cooling.…”

Section: Skin Frictionmentioning

confidence: 99%

Skin Friction Reduction in Hypersonic Turbulent Flow by Boundary Layer Combustion

Suraweera

Mee

Stalker

2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

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“…It is known that injection of gas into a boundary layer can be effective in reducing heat transfer rates and skin friction 17 . This process is often referred to as film cooling.…”

Section: Skin Frictionmentioning

confidence: 99%

Skin Friction Reduction in Hypersonic Turbulent Flow by Boundary Layer Combustion

Suraweera

Mee

Stalker

2005

43rd AIAA Aerospace Sciences Meeting and Exhibit

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“…Among numerous skin friction/ thermal protection techniques [4,5,6], boundary-layer combustion technique, which use a injection and combustion of flammable gas like hydrogen, attracts worldwide attention because of its excellent skin-friction reduction performance.…”

Section: Introductionmentioning

confidence: 99%

Hydrogen Energy paper 17

2018

Proceeding of 2018 the Fourth International Symposium on Hydrogen Energy, Renewable Energy and Materials

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Abstract:The improvement of the skin friction/heat transfer prediction theory of compressible turbulent boundary-layer combustion of hydrogen is conducted in this paper. The original theory is improved through two aspects. One is the modification of the relation between surface hydrogen mass fraction and Reynolds number by rebuilding the Kármán momentum integral relation. The other is the change of computational method of Prandtl number by adopting the molecular kinetic theory. The improved theory is used to make prediction of skin friction and heat transfer that are found to be better consistent with experimental results than original theory. In addition, a numerical experiment of boundary-layer combustion is conducted. By comparing the results given by numerical simulation and theoretical prediction, it also found that the improved theory shows better prediction performance than the original theory.

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“…Moreover, the research on the film cooling [8] revealed that this technique can reduce not only the heat flux but also the skin friction. In 2000, Goyne et al [9] found in experiments that the boundary-layer combustion technique, which uses the slot tangential injection and combustion of hydrogen, can further reduce the skin friction of the hypervelocity turbulent boundary layer compared with the film-cooling technique in which no combustion exists.…”

mentioning

confidence: 98%

“…Film cooling, which can reduce the wall heat flux through injecting low-temperature gas (hydrogen is preferred) into the boundary layer, is an active cooling technique extensively used in high-temperature environments inside engines [7]. Moreover, the research on the film cooling [8] revealed that this technique can reduce not only the heat flux but also the skin friction.…”

mentioning

confidence: 98%

Combustion Heat-Release Effects on Supersonic Compressible Turbulent Boundary Layers

et al. 2015

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Influences of heat release by the hydrogen combustion in supersonic turbulent boundary layers are numerically studied using Reynolds-averaged Navier-Stokes equations. The adopted Reynolds-averaged Navier-Stokes methodology is first validated by comparing the numerical results with the existing experimental data. Studies on the effects of the flame perpendicular position inside the boundary layer reveal that, while the flame is restricted around the edge of the boundary layer, the heat release may slightly reduce rather than increase the wall heat flux because of the suppression effect on the turbulent energy transport due to heat release. However, as the flame moves toward the wall, the skin-friction reduction effect would not be obviously strengthened, but the wall heat flux could be dramatically enhanced by the increase of near-wall chemical reactions. At a given hydrogen mass flow rate, the injection scheme with a higher injection height and a lower injection velocity could be helpful to achieve a larger skinfriction reduction while maintaining a lower wall heat flux. Finally, analysis of the heat-release effects on the velocity law of the wall shows that van Driest's velocity law largely deviates from the computational results, whereas White's velocity law remains close to the numerical results within a region of approximately y < 300. Nomenclature B = law-of-the-wall constant (5.0) c f = local skin friction coefficient c p = specific heat at constant pressure, J∕kg · K D = mass diffusivity, m 2 ∕s E = total energy, J∕kg H = total enthalpy, J∕kg h s = static enthalpy for species s, J∕kg h = hydrogen injection height at the entrance, m k = turbulent kinetic energy, m 2 ∕s 2 M = Mach number Pr = Prandtl number Pr t = turbulent Prandtl number p = pressure, MPa q w = local heat flux, MW∕m 2 r= Pr 1∕3 , recovery factor Sc t = turbulent Schmidt number T = temperature, K u = velocity, m∕s u τ = friction velocity, m∕s Y hw = hydrogen mass fraction at the wall Y s = mass fraction of species s δ = boundary-layer thickness, m κ = von Kármán constant (0.41) λ = molecular thermal conductivity, W∕m · K μ = molecular viscosity, N · s∕m 2 μ t = turbulent eddy viscosity, N · s∕m 2 ρ = density, kg∕m 3 τ = shear stress, N∕m 2 ω = specific turbulent dissipation, 1∕s _ ω = mass production per unit volume per unit time, kg∕m 3 · s Subscripts e = edge of boundary layer j = jet s = species s w = wall ∞ = freestream Superscripts t = turbulent = Reynolds averagẽ = Favrè average

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Film-Cooling Effectiveness and Skin Friction in Hypersonic Turbulent Flow

Cited by 78 publications

References 5 publications

Skin Friction Reduction in Hypersonic Turbulent Flow by Boundary Layer Combustion

Skin Friction Reduction in Hypersonic Turbulent Flow by Boundary Layer Combustion

Hydrogen Energy paper 17

Combustion Heat-Release Effects on Supersonic Compressible Turbulent Boundary Layers

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