View factors for perpendicular and parallel rectangular plates

Ehlert, J.; Smith, Theodore F.

doi:10.2514/3.11587

Cited by 64 publications

(22 citation statements)

References 2 publications

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“…Other phenomena associated with onset of flashover include  Upper layer between 500 -600 °C [6,7] at temperature of 500 °C and using view factors between finite parallel plates [32] and an emissivity of 0.8 gives a value of 13 kW/m 2 at floor level. This would appear lower than expected but it does not account for radiation from the fuel package and the flames through and above it, which can be shown to contribute an additional 4 to 10 kW/m 2 to floor targets depending on the distance from the flamethis part of the calculation was performed using view factors between perpendicular finite rectangles [32], to represent the vertical flame and a target on the floor, a flame temperature of 900 °C and a calculated flame emissivity of 0.5.…”

Section: Onset Of Flashovermentioning

confidence: 99%

Effects of fire-fighting on a fully developed compartment fire: Temperatures and emissions

Alarifi

Dave²,

Phylaktou

et al. 2014

Fire Safety Journal

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Section: Onset Of Flashovermentioning

confidence: 99%

Effects of fire-fighting on a fully developed compartment fire: Temperatures and emissions

Alarifi

Dave²,

Phylaktou

et al. 2014

Fire Safety Journal

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“…This configuration gives an approximate view factor from the coupon to the shroud of 0.333 (Ehlert and Smith, 1992). With shroud and coupon temperatures of 800°C and 20°C, respectively, the coupon irradiance is 22.5 kW/m 2 when surface emissivities of the shroud and coupon are included ( 0 8 .…”

Section: Radiant Heat Testmentioning

confidence: 99%

“…A photograph of the test setup is shown in Appendix Figure A.11.1. The view factor from the shroud to the coupon was calculated as 0.036 using the method of Ehlert and Smith (1992). Ignoring radiative interactions with the surroundings, the spatially averaged coupon irradiation is approximately 30.7 kW/m 2 for a shroud temperature of 1000°C.…”

Section: Piloted Ignition Flame Spread Testmentioning

confidence: 99%

Carbon fiber composite characterization in adverse thermal environments.

Gomez-Vasquez¹,

Brown²,

Hubbard³

et al. 2011

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The behavior of carbon fiber aircraft composites was studied in adverse thermal environments. The effects of resin composition and fiber orientation were measured in two test configurations: 102 by 127 millimeter (mm) test coupons were irradiated at approximately 22.5 kW/m 2 to measure thermal response, and 102 by 254 mm test coupons were irradiated at approximately 30.7 kW/m 2 to characterize piloted flame spread in the vertically upward direction. Carbon-fiber composite materials with epoxy and bismaleimide resins, and uni-directional and woven fiber orientations, were tested. Bismaleimide samples produced less smoke, and were more resistant to flame spread, as expected for high temperature thermoset resins with characteristically lower heat release rates. All materials lost approximately 20-25% of their mass regardless of resin type, fiber orientation, or test configuration. Woven fiber composites displayed localized smoke jetting whereas uni-directional composites developed cracks parallel to the fibers from which smoke and flames emanated. Swelling and delamination were observed with volumetric expansion on the order of 100% to 200%. The purpose of this work was to provide validation data for SNL's foundational thermal and combustion modeling capabilities.

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“…As the enclosure has two perpendicular planes of symmetric, we have considered a one-quarter model. In this model, two symmetric surfaces are specified as totally specular with reflection factor of 1 = was obtained analytically (20) . Then, the radiative heat transfer was obtained by the method can be achieved the same as distribution given by direct solution.…”

Section: Validation Procedures 511 Direct Methodsmentioning

confidence: 99%

Optimal Boundary Design of Radiant Enclosures Using Micro-Genetic Algorithm (Effects of Refractory Properties and Aspect Ratio of Enclosure on Heaters Setting)

Ali

Maruyama

Mansouri

et al. 2008

JTST

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This study presents an optimization methodology for finding the heaters setting that produce a desired heat flux and temperature distribution over a region of the enclosure surface, called the design surface. Radiation element method by ray emission model (REM 2 ) was used to calculate the radiative heat flux on the design surface, which enable us to handle reflecting surfaces. Micro-genetic algorithm was used to minimize an objective function, which was expressed by the sum of square error between estimated and desired heat fluxes on the design surface. The novel features of this methodology were demonstrated by finding the optimal heaters setting of a three dimensional enclosure for three aspect ratio. The effects of refractory properties have been studied as well.

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View factors for perpendicular and parallel rectangular plates

Cited by 64 publications

References 2 publications

Effects of fire-fighting on a fully developed compartment fire: Temperatures and emissions

Effects of fire-fighting on a fully developed compartment fire: Temperatures and emissions

Carbon fiber composite characterization in adverse thermal environments.

Optimal Boundary Design of Radiant Enclosures Using Micro-Genetic Algorithm (Effects of Refractory Properties and Aspect Ratio of Enclosure on Heaters Setting)

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