| タイトル | The Compressible Laminar Boundary Layer with Heat Transfer and Arbitrary Pressure Gradient |
| 本文（外部サイト） | http://hdl.handle.net/2060/19930091005 |
| 著者（英） | Reshotko, Eli; Cohen, Clarence B |
| 著者所属（英） | National Advisory Committee for Aeronautics. Lewis Flight Propulsion Lab. |
| 発行日 | 1956-01-01 |
| 言語 | eng |
| 内容記述 | An approximate method for the calculation of the compressible laminar boundary layer with heat transfer and arbitrary pressure gradient, based on Thwaites' correlation concept, is presented. With the definition of dimensionless shear and heat-transfer parameters and an assumed correlation of these parameters in terms of a momentum parameter, a complete system of relations for calculating skin friction and heat transfer results. Knowledge of velocity or temperature profiles is not necessary in using this calculation method. When the method is applied to a convergent-divergent, axially symmetric rocket nozzle, it shows that high rates of heat transfer are obtained at the initial stagnation point and at the throat of the nozzle. Also indicated are negative displacement thicknesses in the convergent portion of the nozzle; these occur because of the high density within the lower portions of the cooled boundary layer. (author) |
| レポートNO | 93R20295
NACA-TR-1294 |
| 権利 | No Copyright |
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