An Experimental Investigation Of Heat Transfer Effects On Boundary Layer Separation In Supersonic Flow
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An Experimental Investigation of the Effect of Surface Heating on Boundary-layer Transition on a Flat Plate in Supersonic Flow
| Author | : Robert W. Higgins |
| Publisher | : |
| Total Pages | : 38 |
| Release | : 1951 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
Boundary-layer transition has been studied on a heated flat plate in an air stream at a Mach number of 2.40 and a length Reynolds number range from 475,000 to 3,930,000. The transition region was investigated at nominal plate temperature levels of 60, 100, 140, 180, and 260 degrees F and depicted in a series of curves of transition Reynolds numbers, based on boundary-layer dimensions and fluid properties evaluated alternatively at free-stream and wall temperatures. The average skin-friction coefficient over the laminar portion of the boundary layer was determined.
A Review of High-speed, Convective, Heat-transfer Computation Methods
| Author | : Michael E. Tauber |
| Publisher | : |
| Total Pages | : 44 |
| Release | : 1989 |
| Genre | : Aerodynamic heating |
| ISBN | : |
Boundary Layer Effects
| 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.
Measurements of a Supersonic Favorable-pressure-gradient Turbulent Boundary Layer with Heat Transfer
| Author | : Robert L. P. Voisinet |
| Publisher | : |
| Total Pages | : 144 |
| Release | : 1973 |
| Genre | : Fluid mechanics |
| ISBN | : |
The results of a detailed experimental investigation of the compressible turbulent boundary layer in a favorable-pressure-gradient flow are presented for zero, moderate and severe heat-transfer conditions. The studies were conducted on a flat nozzle wall at momentum thickness Reynolds numbers from 6,700 to 56,000 and at three wall-to-adiabatic-wall temperature ratios. An attempt was made to hold values of Clauser's pressure-gradient parameter constant. Complete profile measurements were taken with Pitot pressure probes and conical-equilibrium and fine-wire temperature probes. (Modified author abstract).
