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- W2048287757 abstract "The design of cooled skin panels, which requires consideration of many parameters such as heat load, skin thickness, panel size, tube spacing, tube size, temperature limits, coolant flow, etc., must minimize weight and thermal stresses. A design procedure for such panels has been developed by Bell Aerospace Company (Helenbrook and Anthony, 1971). This design procedure assumes a uniform heating rate to the panel, i.e., the variation of aerodynamic heating rate due to the cyclic wall temperature distribution, which results from the discrete coolant tube locations in such a panel, has been neglected. This study was made to determine if these variations were sufficiently large to cause variations in aerodynamic heating rate which would require coupling of boundary layer and conductive thermal analysis solutions." @default.
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- W2048287757 date "1974-08-01" @default.
- W2048287757 modified "2023-09-26" @default.
- W2048287757 title "Effect of Wall Temperature Spatial Variations on Aerodynamic Heatingto an Actively Cooled Aircraft" @default.
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- W2048287757 doi "https://doi.org/10.2514/3.60373" @default.
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