Heat transfer distributions around nominal ice accretion shapes formed on a cylinder in the NASA Lewis Icing Research Tunnel

Fossen, G. James Van; Simoneau, R. J.; Olsen, W. A.; Shaw, R. J.

doi:10.2514/6.1984-17

Cited by 30 publications

(9 citation statements)

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“…However, the wet/dry ice growth data obtained could be used to compare the ice growth predicted by different heat transfer coefficients in the form Nu = A Re B and the quasi steady-state icing model. Recent experimental heat transfer coefficient measurements about a bare cylinder by Van Fossen et al, 10 in support of the NASA icing research program are compared in this way. The bare cylinder is considered because most of the wet/dry measurements were obtained for relatively small ice thicknesses, and hence, for flowfield purposes, the geometry is essentially that of a bare cylinder.…”

Section: Resultsmentioning

confidence: 99%

“…The study was limited to the stagnation region to avoid mass flux ambiguities which may occur in downstream locations due to water runback. A series of previously measured convective heat transfer coefficients with different levels of freestream turbulence and surface roughness 10 -4-C)" 4-r)" (A\ out V£ conv T *-£ sublimation/evaporation "*" ^ droplet warming v* 4 "/ At steady-state it is assumed that the ice surface achieves a locally uniform equilibrium temperature, T surf . Conduction into the ice is assumed to be zero and chordwise conduction between adjacent control volume is neglected.…”

Section: Introductionmentioning

confidence: 99%

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Comparison of wet and dry growth in artificial and flight icing conditions

Hansman

Kirby

1987

Journal of Thermophysics and Heat Transfer

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The heat transfer behavior of accreting ice surfaces in natural (flight test) and simulated (wind tunnel) cloud icing conditions are studied. Observations of wet and dry ice growth regimes as measured by ultrasonic pulseecho techniques are made. Observed wet and dry ice growth regimes at the stagnation point of a cylinder are compared with those predicted using a quasi steady-state heat balance model. A series of heat transfer coefficients are employed by the model to infer the local heat transfer behavior of the actual ice surfaces. The heat transfer in the stagnation region is generally inferred to be higher in wind tunnel icing tests than in natural, flight icing conditions. NomenclatureA,B -experimentally derived constants (-) Q = specific heat capacity of ice* J/kg K C p -specific heat capacity of air, J/kg K C w = specific heat capacity of water, J/kg K D = diffusion coefficient of water vapor in air, mVs d = cylinder diameter, m h = local convective heat transfer coefficient, W/m 2 K k = thermal conductivity of air, W/m K L f = latent heat of fusion of water, J/kg L s = latent heat of sublimation of water, J/kg L v = latent heat of vaporization of water, J/kg L* = effective latent heat of fusion M" = local mass flux/time, kg/m 2 s Nu -Nusselt number (-) Q " = local heat flux/time, W/m 2 Re = Reynolds number based on cylinder diameter and y (X (-) r = recovery factor, 0.875 (-) A TV = cloud supercooling = -T^ (° C) T'surf = equilibrium surface temperature, °Ĉ = cloud temperature, °C T* = effective surface freestream temperature difference, °C t = icing time, s Fa, = freestream velocity, m/s W = cloud liquid water content, g/m 3 18= local collection efficiency (-) Py,surf = saturated vapor density over surface, kg/m 3 p voo = saturated vapor density in cloud, kg/m 3

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Section: Resultsmentioning

confidence: 99%

Section: Introductionmentioning

confidence: 99%

Comparison of wet and dry growth in artificial and flight icing conditions

Hansman

Kirby

1987

Journal of Thermophysics and Heat Transfer

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“…Its validity was confirmed by Poinsatte 15 and Van Fossen. 16 At the stagnation line of a clean, smooth NACA 0012 airfoil at 0° AOA in the IRT, Poinsatte found (18) are within 10% of the Kreith cylinder coefficients and exponents of equation (17). Van Fossen's clean, smooth cylinder tests for IRT turbulence levels produced a coefficient about 25% higher than Kreith's and a Re exponent within 5%.…”

Section: Energy Balance Similaritymentioning

confidence: 99%

Overview of Icing Physics Relevant to Scaling

Anderson¹,

Tsao²

2003

SAE Technical Paper Series

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“…R_d (4) Where qE_ is the heat added to the gage by the electric heater, q,,a is the heat lost by radiation, qs_p is the heat conducted away from the gage to the epoxy gap and the unguarded ends of the heaters, A is the exposed gage surface area, Van Fossen, et al (1984) for details. The gap loss was about 10 percent of the total heat flow while the radiation heat loss was on the order of 0.2 percent.…”

Section: Heat Transfermentioning

confidence: 99%

Augmentation of Stagnation Region Heat Transfer due to Turbulence From a DLN Can Combustor

Fossen

Bunker

2000

Volume 3: Heat Transfer; Electric Power; Industrial and Cogeneration

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Heat transfer measurements have been made in the stagnation region of a flat plate with a circular leading edge. Electrically heated aluminum strips placed symmetrically about the leading edge stagnation region were used to measure spanwise averaged heat transfer coefficients. The maximum Reynolds number obtained, based on leading edge diameter, was about 100,000. The model was immersed in the flow field downstream of an approximately half scale model of a can-type combustor from a low NOx, ground based power-generating turbine. The tests were conducted with room temperature air; no fuel was added. Room air flowed into the combustor through six vane type fuel/air swirlers. The combustor can contained no dilution holes. The fuel/air swirlers all swirled the incoming airflow in a counter clockwise direction (facing downstream). A 5-hole probe flow field survey in the plane of the model stagnation point showed the flow was one big vortex with flow angles up to 36° at the outer edges of the rectangular test section. Hot wire measurements showed test section flow had very high levels of turbulence, around 28.5%, and had a relatively large axial-length scale-to-leading edge diameter ratio of 0.5. X-wire measurements showed the turbulence to be nearly isotropic. Stagnation heat transfer augmentation over laminar levels was around 77% and was about 14% higher than predicted by a previously developed correlation for isotropic grid generated turbulence.

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Heat transfer distributions around nominal ice accretion shapes formed on a cylinder in the NASA Lewis Icing Research Tunnel

Cited by 30 publications

References 0 publications

Comparison of wet and dry growth in artificial and flight icing conditions

Comparison of wet and dry growth in artificial and flight icing conditions

Overview of Icing Physics Relevant to Scaling

Augmentation of Stagnation Region Heat Transfer due to Turbulence From a DLN Can Combustor

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