The Effects Of Heat Transfer On The Separation Of A Laminar Boundary Layer Under Equilibrium Conditions In Supersonic Flow
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A Review of High-speed, Convective, Heat-transfer Computation Methods
Author | : Michael E. Tauber |
Publisher | : |
Total Pages | : 44 |
Release | : 1989 |
Genre | : Aerodynamic heating |
ISBN | : |
Annual Report - National Advisory Committee for Aeronautics
Author | : United States. National Advisory Committee for Aeronautics |
Publisher | : |
Total Pages | : |
Release | : 1955 |
Genre | : Aeronautics |
ISBN | : |
Includes the Committee's Technical reports no. 1-1058, reprinted in v. 1-37.
Boundary Layer Transition at Supersonic Speeds
Author | : E. R. Van Driest |
Publisher | : |
Total Pages | : 108 |
Release | : 1961 |
Genre | : Aerodynamics, Supersonic |
ISBN | : |
Experiments carried out in the 12-inch supersonic wind tunnel to investigate the effect of three dimensional roughness elements (spheres) on boundary-layer transition on a 10-degree (apex angle) cone without heat transfer are described. The local Mach number for these tests was 2.71. The data show clearly that the minimum (effective) size of trip required to bring transition to its lowest Reynolds number varies power of the distance from the apex of the cone to the trip. Use of available data at other Mach numbers indicates that the Mach number influence for effective tripping is taken into account by a simple expression. Some remarks concerning the roughness variation for transition on a blunt body are made. Finally, a general criterion is introduced which gives insight to the transition phenomenon and anticipates effects of external and internal disturbances, Mach number transfer.
Some Heat Transfer Problems in Hypersonic Flow
Author | : Antonio Ferri |
Publisher | : |
Total Pages | : 72 |
Release | : 1959 |
Genre | : Aerodynamics, Hypersonic |
ISBN | : |
Boundary Layer Separation in the Presence of Heat Transfer
Author | : G. E. Gadd |
Publisher | : |
Total Pages | : 13 |
Release | : 1960 |
Genre | : Boundary layer |
ISBN | : |
Effects of heat transfer on the separation of laminar boundary layers in supersonic flow are considered theoretically and experimentally. In theory, cooling the wall reduces the extent of regions of separation and steepens the pressure gradients, whilst heating the wall has opposite effects. The experimental results partially confirm these predictions. (Author).