Boundary Layer Separation in the Presence of Heat Transfer

Boundary Layer Separation in the Presence of Heat Transfer
Author: G. E. Gadd
Publisher:
Total Pages: 13
Release: 1960
Genre: Boundary layer
ISBN:
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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).

Boundary Layer Effects

Boundary Layer Effects
Author: Anthony W. Fiore
Publisher:
Total Pages: 962
Release: 1978
Genre: Turbulent boundary layer
ISBN:
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In 1975 the U.S. Air Force and the Federal Republic of Germany signed a Data Exchange Agreement numbered AF-75-G-7440 entitled 'Viscous and Interacting Flow Fields.' The purpose was to exchange data in the area of boundary layer research. It includes both experimental and theoretical boundary layer research at speeds from subsonic to hypersonic Mach numbers in the presence of laminar, transitional, and turbulent boundary layers. The main effort in recent years has been on turbulent boundary layers, both attached and separated in the presence of such parameters as pressure gradients, wall temperature, surface roughness, etc. In the United States the research was conducted in various Department of Defense, NASA, aircraft corporations, and various university laboratories. In the Federal Republic of Germany it was carried out within the various DFVLR, industrial, and university research centers.

Boundary Layer Transition at Supersonic Speeds

Boundary Layer Transition at Supersonic Speeds
Author: E. R. Van Driest
Publisher:
Total Pages: 108
Release: 1961
Genre: Aerodynamics, Supersonic
ISBN:
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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.