Flow Visualization Studies Of A Fin Protuberance Partially Immersed In A Turbulent Boundary Layer At Mach 5
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| Author | : Allen Edward Winkelmann |
| Publisher | : |
| Total Pages | : 84 |
| Release | : 1970 |
| Genre | : Flow visualization |
| ISBN | : |
Various flow-visualization results are presented for a cylindrically blunted, unswept fin (yawed and unyawed) partially immersed in a turbulent boundary layer (delta approx. = 2.6 inches). The model, consisting of a fin-flat plate combination, was tested at a nominal Mach number of 5 and nominal free-stream Reynolds numbers per foot of 2800 000 and 7400 000. Azobenzene tests show regions of high heat transfer on the flat plate immediately upstream and downstream of the fin. Oil smear tests show in detail the surface shear directions and locations of separated flow which occur on the model. Schlieren and shadowgraph photographs indicate the complex shock wave structure which exists in front of the fin. A possible flow-field model is suggested to account for the observed flow patterns. (Author).
| Author | : Gillerlain, Jr. (Joseph D.) |
| Publisher | : |
| Total Pages | : 86 |
| Release | : 1976 |
| Genre | : Aerodynamic heating |
| ISBN | : |
The general purpose of this investigation was to study the separated flow field associated with a fin-body juncture. Specific objectives included: (a) determining the severity and extent of aerodynamic heating, (b) providing flow visualization results to illustrate the flow structure, and (c) obtaining a data base of heat-transfer and surface-pressure measurements upon which to develop future analytical relations to predict peak interference heating levels. Tests were conducted at Mach 5 over a unit Reynolds number range of 4.5 to 26 million per foot. A fin-cone model was used. The data consist of surface- pressure distributions, heat-transfer measurements using the phase-change paint technique, and schlieren and oil-flow photographs. Results are presented for several fin-cone geometries to include fin sweep and fin-cone gap. Where possible, comparisons are made with fin-flat-plate data.
| Author | : Anthony W. Fiore |
| Publisher | : |
| Total Pages | : 962 |
| Release | : 1978 |
| Genre | : Turbulent boundary layer |
| ISBN | : |
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.
| Author | : |
| Publisher | : |
| Total Pages | : 922 |
| Release | : 1970 |
| Genre | : Science |
| ISBN | : |
| Author | : Allen E. Winkelmann |
| Publisher | : |
| Total Pages | : 55 |
| Release | : 1970 |
| Genre | : |
| ISBN | : |
Various flow-visualization results are presented for a cylindrically blunted, unswept fin (yawed and unyawed) partially immersed in a turbulent boundary layer (delta approx. = 2.6 inches). The model, consisting of a fin-flat plate combination, was tested at a nominal Mach number of 5 and nominal free-stream Reynolds numbers per foot of 2800 000 and 7400 000. Azobenzene tests show regions of high heat transfer on the flat plate immediately upstream and downstream of the fin. Oil smear tests show in detail the surface shear directions and locations of separated flow which occur on the model. Schlieren and shadowgraph photographs indicate the complex shock wave structure which exists in front of the fin. A possible flow-field model is suggested to account for the observed flow patterns. (Author).
| Author | : E. C. Lemmon |
| Publisher | : |
| Total Pages | : 64 |
| Release | : 1971 |
| Genre | : Space vehicles |
| ISBN | : |
| Author | : Ching Jen Chen |
| Publisher | : CRC Press |
| Total Pages | : 884 |
| Release | : 1987 |
| Genre | : Science |
| ISBN | : 9780891165583 |
| Author | : |
| Publisher | : |
| Total Pages | : 780 |
| Release | : 1971 |
| Genre | : Aeronautics |
| ISBN | : |
| Author | : |
| Publisher | : |
| Total Pages | : 300 |
| Release | : 1972 |
| Genre | : Mechanics, Applied |
| ISBN | : |
| Author | : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development |
| Publisher | : |
| Total Pages | : 500 |
| Release | : 1971 |
| Genre | : Aeronautics |
| ISBN | : |
