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.
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 |
Index of NACA Technical Publications
Title | Index of NACA Technical Publications PDF eBook |
Author | United States. National Advisory Committee for Aeronautics |
Publisher | |
Pages | 388 |
Release | 1959 |
Genre | Aeronautics |
ISBN |
A Selected Listing of NASA Scientific and Technical Reports for ...
Title | A Selected Listing of NASA Scientific and Technical Reports for ... PDF eBook |
Author | |
Publisher | |
Pages | 388 |
Release | 1957 |
Genre | Aeronautics |
ISBN |
Preliminary Results from a Free-flight Investigation of Boundary-layer Transition and Heat Transfer on a Highly Polished 8-inch-diameter Hemisphere-cylinder at Mach Numbers Up to 3 and Reynolds Numbers Based on a Length of 1 Foot Up to 17.7 X 106
Title | Preliminary Results from a Free-flight Investigation of Boundary-layer Transition and Heat Transfer on a Highly Polished 8-inch-diameter Hemisphere-cylinder at Mach Numbers Up to 3 and Reynolds Numbers Based on a Length of 1 Foot Up to 17.7 X 106 PDF eBook |
Author | James R. Hall |
Publisher | |
Pages | 34 |
Release | 1957 |
Genre | Boundary layer |
ISBN |
Annual Report of the National Advisory Committee for Aeronautics
Title | Annual Report of the National Advisory Committee for Aeronautics PDF eBook |
Author | United States. National Advisory Committee for Aeronautics |
Publisher | |
Pages | 1516 |
Release | 1958 |
Genre | Aeronautics |
ISBN |
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
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.