Heat-transfer Rates and Ablation on a Blunted Cylinder-flare Configuration in Free Flight Up to a Mach Number of 8.98
Author | : Clyde W. Winters |
Publisher | : |
Total Pages | : 40 |
Release | : 1964 |
Genre | : Ablative materials |
ISBN | : |
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Author | : Clyde W. Winters |
Publisher | : |
Total Pages | : 40 |
Release | : 1964 |
Genre | : Ablative materials |
ISBN | : |
Author | : Clyde W. Winters |
Publisher | : |
Total Pages | : 56 |
Release | : 1964 |
Genre | : Ablative materials |
ISBN | : |
Author | : Charles R. Rumsey |
Publisher | : |
Total Pages | : 66 |
Release | : 1961 |
Genre | : Fluid mechanics |
ISBN | : |
Author | : Charles B. Rumsey |
Publisher | : |
Total Pages | : 26 |
Release | : 1955 |
Genre | : Aerodynamic heating |
ISBN | : |
Aerodynamic-heat-transfer measurements have been made at a station on the 10 degree total angle conical nose of a rocket-propelled model at flight Mach numbers of 1.4 to 3.9. The corresponding values of local Reynolds number varied from 18,000,000 to 46,000,000 and the ratio of skin temperature to local static temperature varied from 1.2 to 2.4. The experimental data, reduced to Stanton number, were in fair agreement with values predicted by Van Driest's theory for heat transfer on a cone with turbulent flow from the nose tip.
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.
Author | : Charles R. Rumsey |
Publisher | : |
Total Pages | : 61 |
Release | : 1961 |
Genre | : Aerodynamics, aircraft |
ISBN | : |
Author | : Howard S. Carter |
Publisher | : |
Total Pages | : 38 |
Release | : 1961 |
Genre | : Aerodynamic heating |
ISBN | : |
Heat-transfer rates have been measured in free flight along the stagnation line of an unswept cylinder mounted transversely on an axial cylinder so that the shock wave from the hemispherical nose of the axial cylinder intersected the bow shock of the unswept transverse cylinder. Data were obtained at Mach numbers from 2.53 to 5.50 and at Reynolds numbers based on the transverse cylinder diameter from 1.00 x 106 to 1.87 x 106. Shadowgraph pictures made in a wind tunnel showed that the flow field was influenced by boundary-layer separation on the axial cylinder and by end effects on the transverse cylinder as well as by the intersecting shocks. Under these conditions, the measured heat-transfer rates had inconsistent variations both in magnitude and distribution which precluded separating the effects of these disturbances. The general magnitude of the measured heating rates at Mach numbers up to 3 was from 0.1 to 0.5 of the theoretical laminar heating rates along the stagnation line for an infinite unswept cylinder in undisturbed flow. At Mach numbers above 4 the measured heating rates were from 1.5 to 2 times the theoretical rates.