Investigation Of The Development Of Laminar Boundary Layer Instabilities Along A Sharp Cone
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| Author | : J. C. Donaldson |
| Publisher | : |
| Total Pages | : 62 |
| Release | : 1985 |
| Genre | : |
| ISBN | : |
Download Investigation of the Development of Laminar Boundary-Layer Instabilities Along a Sharp Cone Book in PDF, Epub and Kindle
Measurements of mean-flow and fluctuating-flow parameters were made in the boundary layer on a sharp 7-deg cone in an investigation of the stability of laminar boundary layers. The flow fluctuation measurements were made using hot-wire anemometry techniques. Flow field profiles and model surface conditions were also measured. The testing was performed at a free-stream Mach number of 8 for free-stream Unit-Reynolds numbers of 1.0-, 2.0-, and 3.0-million per foot. The test equipment and techniques and the data acquisition and reduction procedures are described. Analysis of the hot-wire anemometer data is beyond the scope of this report. Keywords: Hypersonic/flow; Sharp cones; Wind tunnel tests; Boundary-layer stability.
| Author | : J. C. Donaldson |
| Publisher | : |
| Total Pages | : 51 |
| Release | : 1988 |
| Genre | : |
| ISBN | : |
Download Investigation of the Development of Laminar Boundary-Layer Instabilities Along a Cooled-Wall Cone in Hypersonic Flows Book in PDF, Epub and Kindle
Measurements of fluctuating flow and mean flow parameters were made in the boundary layer on a cooled wall, sharp 7-deg (half-angle) cone in an investigation of wall temperature effects on the stability of laminar boundary layers in hypersonic flow. The flow fluctuation measurements were made using constant-current hot-wire anemometry techniques. Boundary-layer profiles and cone surface conditions were measured to supplement the hot-wire data. Testing was done at Mach numbers 8 and 6 with a free-stream unit Reynolds number of 1.0-million per foot. The test equipment, test techniques, and the data acquisition and reduction procedures are described. Analysis of the hot wire anemometer data is beyond the scope of this report. Hypersonic flow, Wind tunnel tests, Cold wall model, Boundary layer stability, Hot wire anemometry, Sharp cone. (mjm).
| Author | : J. C. Donaldson |
| Publisher | : |
| Total Pages | : 56 |
| Release | : 1988 |
| Genre | : |
| ISBN | : |
Download Investigation of the Development of Laminar Boundary-Layer Instabilities Along a Blunted Cone Book in PDF, Epub and Kindle
Measurements of mean-flow and fluctuating-flow parameters were made in the boundary layer of a spherically blunted (0.7-in. radius), 7-deg (half-angle) cone in an investigation of the stability of laminar boundary layers. The flow-fluctuation measurements were made using hot-wire anemometry techniques. Flow-field profiles and model surface pressures were also measured. The testing was performed at free-stream Mach number 8 with a free-stream unit Reynolds number of 1.6-million per foot. The test equipment and techniques, and the data acquisition and reduction procedures are described. Analysis of the hot-wire anemometer data is beyond the scope of this report. Hypersonic flow, Blunt cone, Wind tunnel tests, Laminar boundary-layer surveys, Hot-wire anemometry, Boundary-layer stability. (jes).
| Author | : K. F. Stetson |
| Publisher | : |
| Total Pages | : 8 |
| Release | : 1984 |
| Genre | : |
| ISBN | : |
Download An Experimental Investigations of the Stability of the Laminar Boundary Layer on a Cone at M Book in PDF, Epub and Kindle
The stability of the laminar boundary layer on a 7-degree half angle cone at M infinity = 8 was experimentally investigated using hot-wire anemometry techniques. The principle instability of the hypersonic boundary layer was associated with second mode disturbances. The frequency of the most amplified disturbances was directly related to the boundary layer thickness. Small nosetip bluntness was found to make significant changes, compared to a sharp cone, in the stability characteristics of the boundary layer.
| Author | : |
| Publisher | : |
| Total Pages | : 702 |
| Release | : 1995 |
| Genre | : Aeronautics |
| ISBN | : |
Download Scientific and Technical Aerospace Reports Book in PDF, Epub and Kindle
| Author | : Michael C. Fischer |
| Publisher | : |
| Total Pages | : 76 |
| Release | : 1970 |
| Genre | : Aerodynamics |
| ISBN | : |
Download An Experimental Investigation of Boundary-layer Transition on a 10 ̊half-angle Cone at Mach 6.9 Book in PDF, Epub and Kindle
Boundary layer transition on nose cones at hypersonic speeds.
| Author | : North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development |
| Publisher | : |
| Total Pages | : 124 |
| Release | : 1965 |
| Genre | : Aerodynamics |
| ISBN | : |
Download Recent Developments in Boundary Layer Research Book in PDF, Epub and Kindle
| Author | : Roger L. Kimmel |
| Publisher | : |
| Total Pages | : 46 |
| Release | : 1993 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
Download The Effect of Pressure Gradients on Transition Zone Length in Hypersonic Boundary Layers Book in PDF, Epub and Kindle
Boundary layer transition was measured in zero, favorable, and adverse pressure gradients at Mach 8 using heat transfer. Models consisted of 7 degrees half angle forecones 0.4826 m long, followed by flared or ogive aft bodies 0.5334 m long. The flares and ogives produced constant pressure gradients. For the cases examined, favorable pressure gradients delay transition and adverse pressure gradients promote transition, but transition zone lengths are shorter in favorable pressure gradient. Results of the effect of adverse pressure gradient on transition zone lengths were inconclusive.
| Author | : Raul Jorge Conti |
| Publisher | : |
| Total Pages | : 38 |
| Release | : 1961 |
| Genre | : Heat |
| ISBN | : |
Download Laminar Heat-transfer and Pressure Measurements at a Mach Number of 6 on a Sharp and Blunt 15° Half-angle Cones at Angles of Attack Up to 90° Book in PDF, Epub and Kindle
Two circulation conical configurations having 15° half-angles were tested in laminar boundary layer at a Mach number of 6 and angles of attack up to 90°. One cone had a sharp nose and a fineness ratio of 1.87 and the other had a spherically blunted nose with a bluntness ratio of 0.1428 and a fineness ratio of 1.66. Pressure measurements and schlieren pictures of the flow showed that near-conical flow existed above 70° high pressure areas were present near the base and the bow shock wave was considerably curved.
| Author | : Kenneth F. Stetson |
| Publisher | : |
| Total Pages | : 116 |
| Release | : 1990 |
| Genre | : Aerodynamics, Hypersonic |
| ISBN | : |
Download Comments on Hypersonic Boundary-layer Transition Book in PDF, Epub and Kindle
This is a survey paper on the subject of hypersonic boundary-layer transition. Part 1 discusses boundary-layer stability theory, hypersonic boundary-layer stability experiments, and a comparison between theory and experiment. Part 2 contains comments on how many configuration and flow parameters influence transition. Part 3 discusses some additional general aspects of transition. Part 4 discusses problems of predicting transition and comments on three prediction methods. Part 5 contains some general guidelines for prediction methodology. Keywords: Boundary layer transition, Boundary layer stability, Hypersonic boundary layers.
