Thermophysical Properties Research Literature Retrieval Guide Edited by Y. S. Touloukian, J. K. Gerritsen and N. Y. Moore Second edition, revised and expanded. Book 1: Pp. xxi + 819. Book 2: Pp.621. Book 3: Pp. ix + 1315. (New York: Plenum Press, 1967.) n.p.

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Heat and Mass Transfer

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Electronic Transport In Mesoscopic Systems

Review of spray cooling – Part 1: Single-phase and nucleate boiling regimes, and critical heat flux

Nomenclature Ac = accumulation parameter Cd drag coefficient Ci = lift coefficient Cm = moment coefficient Cp = pressure coefficient c = specific heat at constant pressure, J/(kg-K); airfoil chord, m D = propeller diameter, m; flexural stiffness, N-m D drag force, N d = droplet diameter, m E = total collection efficiency / = freezing fraction g = acceleration caused from gravity, m/s Hi = ice thickness, m Hp = plate thickness, m h = airfoil projected height, m hc = convective heat transfer coefficient, W/(m-K) hfg = heat of vaporization, J/kg hsi = heat of fusion, J/kg / = airfoil drag constant K = thermal conductivity, W/(m-K); inertia parameter K0 = modified inertia parameter k = roughness diameter, m LWC = liquid water content, kg/m M = local Mach number MVD = median volume droplet diameter, m m = mass, kg ra = mass flow rate, kg/s m' = mass flow rate per unit width, kg/(m-s) m" = mass flux, kg/(m-s) n = normal direction P = pressure, Pa p spatial pressure distribution, N/m <2 = heat rate, W q = normal pressure distribution, N/m

Aircraft Anti-Icing and De-Icing Techniques and Modeling

A Review of High-Heat-Flux Heat Removal Technologies

This paper discusses the testing of a single-phase spray cooling system that was flown on the NASA KC-135 Reduced-Gravity Research Aircraft. An experimental package, consisting of a spray chamber coupled to a fluid delivery loop system, was fabricated for variable gravity flight tests. The spray chamber contains two opposing nozzles spraying on Indium Tin Oxide (ITO) heaters. These heaters are mounted on glass posts, which are part of a sump system to remove unconstrained liquid from the test chamber. Thermocouples mounted in and around the posts were used to determine both the heat loss through the underside of the ITO heater and the heat extracted by the spray. During flight tests, for Weber numbers of We = 771 ± 19 and 757 ± 15, the non-dimensional heat input was varied from G∆ = 30 to 110 for the non-dimensional grouping (Fr 1/2 Ga) 1/2 = 20 to 66. Flight test data and terrestrial data were compared to analytical and numerical solutions in order to evaluate the heat transfer in the heater and support structure. In general, the Nusselt number at the heater surface was found to decrease with increasing (Fr 1/2 Ga) 1/2 .

Variable-Gravity Effects on a Single-Phase Partially-Confined Spray Cooling System

An experiment has been developed to examine the behavior of a titanium-water loop heat pipe under standard and elevated acceleration fields. The loop heat pipe was mounted on a 2.44 meter-diameter centrifuge table on edge with heat applied to the evaporator via a mica heater and heat rejected using a high-temperature polyalphaolefin oil coolant loop. The loop heat pipe was tested under the following parametric ranges: heat load at the evaporator 100 ≤ Q in ≤ 600 W, heat load at the compensation chamber 0 ≤ Q cc ≤ 50 W, radial acceleration 0 ≤ a r ≤ 10 g. For stationary operation, the evaporative heat transfer coefficient decreased monotonically with heat load whereas the thermal resistance decreased to a minimum then increased. Heat input to the compensation chamber was found to increase the evaporative heat transfer coefficient and decrease the thermal resistance for Q in = 500 W. Transient periodic flow reversal in the loop heat pipe was found for some cases, which was likely due to vapor bubble formation in the primary wick. Operation in an elevated acceleration environment revealed that dry out was dependent on both Q in and a r , and the ability for the loop heat pipe to reprime after an acceleration event that induced dry out was influenced by the evaporator temperature. The evaporative heat transfer coefficient and thermal resistance were found not to be significantly dependent on radial acceleration. However, the evaporator wall superheat was found to increase slightly with radial acceleration at high heat loads.

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Titanium-Water Loop Heat Pipe Operating Characteristics Under Standard and Elevated Acceleration Fields

Quasi-Steady-State Performance of a Heat Pipe Subjected to Transient Acceleration Loadings

The objective ofthis paper was to investigate the cooling performance of 16-nozzle spray array using FC-72 as the working fluid in variable-gravity conditions. A flight-test experiment was modified to accommodate a 16-nozzle spray array, which was then tested in the parabolic flight trajectory environment of NASA's C-9 reduced-gravity aircraft. The 16-nozzle array was designed to cool a 25.4 x 25.4 mm 2 area on a thick-film resistive heater used to simulate an electronic component. Flight tests were conducted over the course of two flight weeks (each week consisting of four flights and each flight consisting of 40 to 60 parabolas). The mass flow rate through the 16-nozzle spray array ranged from 13.1 ≤ m ≤ 21.3 g/s. The heat flux at the thick-film resistor ranged from 2.9 ≤ q" ≤ 25 w / 2 , the subcooling of the working fluid ranged from 1.6 ≤ ΔT sc ≤ 18.4°C, the saturation temperature ranged from 37.4 ≤ T sat ≤ 47.2°C, and the absorbed air content in the working fluid was C = 10.1,14.3 and 16.8% by volume. The spray chamber pressure ranged from 42 ≤ P ≤ 78 kPa and the acceleration ranged from -0.02 ≤ a ≤ -2.02 g. Two-phase cooling was emphasized, but some single-phase data were also collected. A one-dimensional model was used to predict the heater surface temperature from the heat input and mean heater base temperature. It was found that the cooling performance was enhanced in microgravity over terrestrial and elevated gravity. In addition, a sudden degradation in performance was found at high mass flow rates in microgravity, possibly due to liquid buildup on the surface between the nozzle impact zones. A high degree of subcooling was found to be beneficial, but the dissolved air content had little effect on the heat transfer performance in either microgravity or elevated gravity.

Cooling Performance of a 16-Nozzle Array in Variable Gravity

: Baseline tests were performed for a spray cooling system using subcooled fluid under terrestrial gravity conditions, and a steady state numerical model of the glass heater pedestal assembly was built using ANSYS finite element software. A parametric study was performed to study the effects of volumetric flow rate, heat transfer rate, and orientation with respect to gravity on the experimental system. The numerical model data was compared with the experimental data in order to determine the spray heat transfer coefficient along the top of the heated surface. For a volumetric flow range gal/hr and a heat load range of W, the estimated spray heat transfer coefficient was on the order of W/(m2-K), regardless of heater orientation. In addition, the heat lost due to conduction in the upward-facing heater pedestal was estimated using both experimental and numerical results, and was found to be 1.0 greater or less than (percent of heat loss due to conduction in glass heater pedestal assembly) greater or less than 2.5%.

Kirk L. Yerkes

Papers

Variable-Gravity Effects on a Single-Phase Partially-Confined Spray Cooling System

Titanium-Water Loop Heat Pipe Operating Characteristics Under Standard and Elevated Acceleration Fields

Quasi-Steady-State Performance of a Heat Pipe Subjected to Transient Acceleration Loadings

Cooling Performance of a 16-Nozzle Array in Variable Gravity

Experimental Testing and Numerical Modeling of Spray Cooling Under Terrestrial Gravity Conditions