Measurements Of Hypersonic Turbulent Heat Transfer On A Highly Cooled Cone
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| Author | : Donald M. Wilson |
| Publisher | : |
| Total Pages | : 94 |
| Release | : 1967 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
Turbulent boundary layer heat transfer rates were measured on a thin-walled slender cone at a free-stream Mach number of 5.0. Wall to stagnation temperature ratios from 0.15 to 0.40 were obtained by pre-cooling the model using liquid nitrogen. Tests at a wide range of Reynolds numbers were conducted by varying the tunnel supply pressure; thus providing data for both laminar and mixed laminar-turbulent types of boundary layers. The experimental results obtained were compared with existing theories which predict convective heat transfer coefficients. These comparisons indicate that the data corresponding to a 760R supply temperature verify the predictions of Winkler and Cha; however, data acquired at a supply temperature of 1160R substantiate the predictions of Spalding and Chi. (Author).
| Author | : Donald M. Wilson |
| Publisher | : |
| Total Pages | : 63 |
| Release | : 1967 |
| Genre | : |
| ISBN | : |
Turbulent boundary layer heat transfer rates were measured on a thin-walled slender cone at a free-stream Mach number of 5.0. Wall to stagnation temperature ratios from 0.15 to 0.40 were obtained by pre-cooling the model using liquid nitrogen. Tests at a wide range of Reynolds numbers were conducted by varying the tunnel supply pressure; thus providing data for both laminar and mixed laminar-turbulent types of boundary layers. The experimental results obtained were compared with existing theories which predict convective heat transfer coefficients. These comparisons indicate that the data corresponding to a 760R supply temperature verify the predictions of Winkler and Cha; however, data acquired at a supply temperature of 1160R substantiate the predictions of Spalding and Chi. (Author).
| Author | : |
| Publisher | : |
| Total Pages | : 0 |
| Release | : 1966 |
| Genre | : |
| ISBN | : |
Turbulent heat-transfer rates were measured on a thin-walled, slender cone in a hypersonic tunnel at a free-stream Mach number of 5.0. Wall-to-stagnation temperature ratios of approximately 0.3 and 0.45 were obtained by cooling the model with liquid CO2. A wide range of test Reynolds numbers were obtained by varying the tunnel supply pressure. This provided data for both laminar and mixed laminar - turbulent boundary-layer conditions. The experimental results are compared with existing theories which predict convective heat-transfer coefficients. These comparisons substantiate the predictions of Winkler and Cha for the present test conditions. (Author).
| Author | : Donald M. Wilson |
| Publisher | : |
| Total Pages | : 49 |
| Release | : 1966 |
| Genre | : |
| ISBN | : |
Turbulent heat-transfer rates were measured on a thin-walled, slender cone in a hypersonic tunnel at a free-stream Mach number of 5.0. Wall-to-stagnation temperature ratios of approximately 0.3 and 0.45 were obtained by cooling the model with liquid CO2. A wide range of test Reynolds numbers were obtained by varying the tunnel supply pressure. This provided data for both laminar and mixed laminar - turbulent boundary-layer conditions. The experimental results are compared with existing theories which predict convective heat-transfer coefficients. These comparisons substantiate the predictions of Winkler and Cha for the present test conditions. (Author).
| Author | : Kuei-Yuan Chien |
| Publisher | : |
| Total Pages | : 46 |
| Release | : 1973 |
| Genre | : Cone |
| ISBN | : |
Turbulent skin-friction coefficients directly measured on an axisymmetric five-degree-half-angle sharp cone by two floating-element skin-friction balances at a free-stream Mach number of 7.9 are presented. Heat-transfer distributions are obtained simultaneously. These results yield directly the Reynolds analogy factor. Experimental data are used to evaluate four predictive methods. Except for the relatively low-Reynolds-number case, the directly measured sharp-cone Reynolds analogy factor is between 1.01 and 1.07, which is in good agreement with recent flat-plate measurements. Results indicate that the Stanton Number is essentially constant for one range and decreases by about 10 percent in another. (Modified author abstract).
| Author | : |
| Publisher | : |
| Total Pages | : 836 |
| Release | : 1994 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : Jerome D. Julius |
| Publisher | : |
| Total Pages | : 32 |
| Release | : 1959 |
| Genre | : Heat |
| ISBN | : |
| Author | : Charles B. Rumsey |
| Publisher | : |
| Total Pages | : 42 |
| Release | : 1956 |
| Genre | : Aerodynamics |
| ISBN | : |
Abstract: Aerodynamic heat-transfer measurements were at six stations on the 40-inch-long 10° total-angle conical nose of a rocket-propelled model which was flight tested at Mach numbers up to 5.9. The range of local Reynolds number was from 6.6 x 106 to 55.2 x 106. Laminar, transitional, and turbulent heat-transfer coefficients were measured, and, in general, the laminar and turbulent measurements were in good agreement with theory for cones. Experimental transition Reynolds numbers varied from less than 8.5 x 106 to 19.4 x 106. At a relatively constant ratio of wall temperature to local static temperature near 1.2, the transition Reynolds number increased from 9.2 x 106 to 19.4 x 106 as Mach number increased from 1.57 to 3.38. At Mach numbers near 3.7, the transition Reynolds number decreased as the skin temperature increased toward adiabatic wall temperatures.
| Author | : Donald M. Wilson |
| Publisher | : |
| Total Pages | : 82 |
| Release | : 1969 |
| Genre | : Heat |
| ISBN | : |
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 | : Victor Zakkay |
| Publisher | : |
| Total Pages | : 86 |
| Release | : 1962 |
| Genre | : Boundary layer |
| ISBN | : |
A modified equation for the heat transfer coefficient in the transitional and fully turbulent region based on the F.P.R.E. method is then presented. This method gives good agreement with the experimental results presented here.
