A Correlation of Heat-transfer and Skin-friction Data and an Experimental Reynolds Analogy Factor for Highly Cooled Turbulent Boundary Layers at Mach 5.0 PDF Download
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Author: Donald M. Wilson
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 82
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Book Description
Turbulent boundary-layer heat transfer and skin-friction coefficients were measured on sharp slender cones at a free-stream Mach number of 5.0. Wall-to-stagnation temperature ratios from 0.15 to 0.80 were obtained by precooling or preheating the model. Tests were conducted for a wide range of Reynolds numbers by varying the tunnel supply pressure and temperature, thus providing data for naturally turbulent boundary layers. The experimental results were compared with existing theories which predict convective Stanton number or skin-friction coefficients. These comparisons indicate that the heat-transfer data are best predicted by the Spalding-Chi law and the skin friction by the Sommer-Short reference temperature method. The experimental Reynolds analogy factor is adequately predicted by Colburn's incompressible correlation for wall-to-stagnation temperature ratios above about 0.5. However, for lower wall temperature ratios, the experimental Reynolds analogy factor decreases with decreased temperature ratios in a manner which has not been previously reported. (Author).
Author: Donald M. Wilson
Publisher:
ISBN:
Category : Heat
Languages : en
Pages : 82
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Book Description
Turbulent boundary-layer heat transfer and skin-friction coefficients were measured on sharp slender cones at a free-stream Mach number of 5.0. Wall-to-stagnation temperature ratios from 0.15 to 0.80 were obtained by precooling or preheating the model. Tests were conducted for a wide range of Reynolds numbers by varying the tunnel supply pressure and temperature, thus providing data for naturally turbulent boundary layers. The experimental results were compared with existing theories which predict convective Stanton number or skin-friction coefficients. These comparisons indicate that the heat-transfer data are best predicted by the Spalding-Chi law and the skin friction by the Sommer-Short reference temperature method. The experimental Reynolds analogy factor is adequately predicted by Colburn's incompressible correlation for wall-to-stagnation temperature ratios above about 0.5. However, for lower wall temperature ratios, the experimental Reynolds analogy factor decreases with decreased temperature ratios in a manner which has not been previously reported. (Author).
Author: Donald M. Wilson
Publisher:
ISBN:
Category :
Languages : en
Pages : 57
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Book Description
Turbulent boundary-layer heat transfer and skin-friction coefficients were measured on sharp slender cones at a free-stream Mach number of 5.0. Wall-to-stagnation temperature ratios from 0.15 to 0.80 were obtained by precooling or preheating the model. Tests were conducted for a wide range of Reynolds numbers by varying the tunnel supply pressure and temperature, thus providing data for naturally turbulent boundary layers. The experimental results were compared with existing theories which predict convective Stanton number or skin-friction coefficients. These comparisons indicate that the heat-transfer data are best predicted by the Spalding-Chi law and the skin friction by the Sommer-Short reference temperature method. The experimental Reynolds analogy factor is adequately predicted by Colburn's incompressible correlation for wall-to-stagnation temperature ratios above about 0.5. However, for lower wall temperature ratios, the experimental Reynolds analogy factor decreases with decreased temperature ratios in a manner which has not been previously reported. (Author).
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 684
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Book Description
Author: Edward J. Hopkins
Publisher:
ISBN:
Category : Cone
Languages : en
Pages : 34
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Book Description
Skin friction and heat transfer data for hypersonic turbulent layer on flat plates, wind tunnel wall, and cones.
Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 1572
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Book Description
Author: United States. National Advisory Committee for Aeronautics
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1338
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 252
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Book Description
Author: Michael E. Tauber
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 44
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Book Description
Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 818
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Book Description
Author: Coleman duP. Donaldson
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 26
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Book Description
Abstract: The method presented in NACA TN 2692 for evaluating the skin friction of a turbulent boundary layer in compressible flow on an insulated surface is extended to evaluate the turbulent skin friction and heat transfer in compressible flow on a surface which is heated or cooled. The results of this analysis are in good agreement with the heat transfers measured in flight on the NACA RM-10 missile up to Mach number of 3.8.
