Heat-transfer Characteristics of a Hemisphere Cylinder at Hypersonic Mach Numbers
Title | Heat-transfer Characteristics of a Hemisphere Cylinder at Hypersonic Mach Numbers PDF eBook |
Author | E. M. WINKLER |
Publisher | |
Pages | 39 |
Release | 1957 |
Genre | |
ISBN |
Heat-transfer Characteristics of a Hemisphere Cylinder at Hypersonic Mach Numbers
Title | Heat-transfer Characteristics of a Hemisphere Cylinder at Hypersonic Mach Numbers PDF eBook |
Author | E. M. Winkler |
Publisher | |
Pages | 0 |
Release | 1957 |
Genre | Laminar boundary layer |
ISBN |
The heat-transfer characteristics of the laminar compressible boundary layer on a hemisphere cylinder have been investigated at free-stream Mach numbers of 5, 6.5, and 8. The Reynolds number based on free-stream conditions and model diameter was varied from 70,000 to 700,000. Various conditions of steady-state heat trasnfer to the model were realized by circulating a coolant through the model, and by varing the tunnel supply air temperature. The wall to stagnation termperature ratio was varied from 0.43 to 0.75. Optical observations and Pitot pressure surveys of the boundary layer showed it to be laminar on both the hemisphere and the cylindrical afterbody. The heat transfer was evaluated from the temperature differences measured across the model wall under steady-state conditions. Over the hemisphere, the local non-dimensional heat-transfer parameters are, on the average, approximately twnty percent larger than predicted for an isothermal body by Korobkin's modified incompressible theory.
Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.8
Title | Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hypersonic Tunnel at a Mach Number of 6.8 PDF eBook |
Author | Davis H. Crawford |
Publisher | |
Pages | 680 |
Release | 1956 |
Genre | Aeronautics |
ISBN |
At the stagnation point, the theory of Sibulkin, using the diameter and conditions behind the normal shock, was in good agreement with the experiment when the velocity graident at the stagnation opint appropriate to the free-stream Mach number was used.
Effect of Roughness on Heat Transfer to Hemisphere Cylinders at Mach Numbers 10.4 and 11.4
Title | Effect of Roughness on Heat Transfer to Hemisphere Cylinders at Mach Numbers 10.4 and 11.4 PDF eBook |
Author | James C. Dunavant |
Publisher | |
Pages | 44 |
Release | 1967 |
Genre | Aerodynamic heating |
ISBN |
Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hyoersonic Tunnel at a Mach Number of 6.8
Title | Investigation of the Laminar Aerodynamic Heat-transfer Characteristics of a Hemisphere-cylinder in the Langley 11-inch Hyoersonic Tunnel at a Mach Number of 6.8 PDF eBook |
Author | Davis H. Crawford |
Publisher | |
Pages | 21 |
Release | 1957 |
Genre | |
ISBN |
Heat-transfer Characteristics of Blunt Two-and Three-dimensional Bodies at Supersonic Speeds
Title | Heat-transfer Characteristics of Blunt Two-and Three-dimensional Bodies at Supersonic Speeds PDF eBook |
Author | Glen Goodwin |
Publisher | |
Pages | 22 |
Release | 1956 |
Genre | Ablation (Aerothermodynamics) |
ISBN |
Heat-transfer and Pressure Distributions at Mach Numbers of 6.0 and 9.6 Over Two Reentry Configurations for the Five-stage Scout Vehicle
Title | Heat-transfer and Pressure Distributions at Mach Numbers of 6.0 and 9.6 Over Two Reentry Configurations for the Five-stage Scout Vehicle PDF eBook |
Author | Paul F. Holloway |
Publisher | |
Pages | 64 |
Release | 1963 |
Genre | Aerothermodynamics |
ISBN |