Flow Visualization by Elastic Light Scattering in the Boundary Layer of a Supersonic Flow PDF Download
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Author: G. C. Herring
Publisher: DIANE Publishing
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 30
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Book Description
We demonstrate instantaneous flow visualization of the boundary layer region of a Mach 2.5 supersonic flow over a flat plate that is interacting with an impinging shock wave. Tests were performed in the Unitary Plan Wind Tunnel (UPWT) at NASA Langley Research Center. The technique is elastic light scattering using 10-nsec laser pulses at 532 nm. We emphasize that no seed material of any kind, including water (H2O), is purposely added to the flow. The scattered light comes from a residual impurity that normally exists in the flow medium after the air drying process. Thus, the technique described here differs from the traditional vapor-screen method, which is typically accomplished by the addition of extra H2O vapor to the airflow. The flow is visualized with a series of thin two-dimensional light sheets (oriented perpendicular to the streamwise direction) that are located at several positions downstream of the leading edge of the model. This geometry allows the direct observation of the unsteady flow structure in the spanwise dimension of the model and also allows the indirect observation of the boundary layer growth in the streamwise dimension.
Author: G. C. Herring
Publisher: DIANE Publishing
ISBN: 1428990690
Category : Aerodynamics, Supersonic
Languages : en
Pages : 28
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Book Description
We demonstrate instantaneous flow visualization of the boundary layer region of a Mach 2.5 supersonic flow over a flat plate that is interacting with an impinging shock wave. Tests were performed in the Unitary Plan Wind Tunnel (UPWT) at NASA Langley Research Center. The technique is elastic light scattering using 10-nsec laser pulses at 532 nm. We emphasize that no seed material of any kind, including water (H2O), is purposely added to the flow. The scattered light comes from a residual impurity that normally exists in the flow medium after the air drying process. Thus, the technique described here differs from the traditional vapor-screen method, which is typically accomplished by the addition of extra H2O vapor to the airflow. The flow is visualized with a series of thin two-dimensional light sheets (oriented perpendicular to the streamwise direction) that are located at several positions downstream of the leading edge of the model. This geometry allows the direct observation of the unsteady flow structure in the spanwise dimension of the model and also allows the indirect observation of the boundary layer growth in the streamwise dimension.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781723726767
Category : Science
Languages : en
Pages : 30
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Book Description
We demonstrate instantaneous flow visualization of the boundary layer region of a Mach 2.5 supersonic flow over a flat plate that is interacting with an impinging shock wave. Tests were performed in the Unitary Plan Wind Tunnel (UPWT) at NASA Langley Research Center. The technique is elastic light scattering using 10-nsec laser pulses at 532 nm. We emphasize that no seed material of any kind, including water (H2O), is purposely added to the flow. The scattered light comes from a residual impurity that normally exists in the flow medium after the air drying process. Thus, the technique described here differs from the traditional vapor-screen method, which is typically accomplished by the addition of extra H2O vapor to the airflow. The flow is visualized with a series of thin two-dimensional light sheets (oriented perpendicular to the streamwise direction) that are located at several positions downstream of the leading edge of the model. This geometry allows the direct observation of the unsteady flow structure in the spanwise dimension of the model and also allows the indirect observation of the boundary layer growth in the streamwise dimension.Herring, G. C. and Hillard, Mervin E., Jr.Langley Research CenterFLOW VISUALIZATION; ELASTIC SCATTERING; BOUNDARY LAYERS; SUPERSONIC FLOW; AIR FLOW; WIND TUNNELS; WATER; VAPORS; UNSTEADY FLOW; SUPERSONIC SPEED; PULSED LASERS; LEADING EDGES
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Richard M. Wood
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 104
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Book Description
Author: Edward J. Hopkins
Publisher:
ISBN:
Category : Boundary layer control
Languages : en
Pages : 28
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Book Description
Author: Reazul Huq
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 188
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Book Description
The report deals with one way of generating an unsteady flow past a body -- breaking the diaphragm of a shock tube. A visualization of the phenomenon within the boundary layer of such a flow was attempted by using bubbles. A method has been suggested for further work in this line. An unsteady flow was then generated using water as the flow medium in a towing tank following the principles of Ahlborn. Various improvements have led to an experiment that can visualize the details of flow within the boundary layer. The technique has been successfully applied to the case of unsteady flow past a flat plate.
Author: Colin Phillip Coleman
Publisher:
ISBN:
Category :
Languages : en
Pages : 212
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Book Description
Author: Christopher John Bartlett
Publisher:
ISBN:
Category :
Languages : en
Pages : 190
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Book Description
Author: Gregory C. Herring
Publisher:
ISBN:
Category : Raman effect
Languages : en
Pages : 26
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Book Description
Using a pulsed Nd:YAG laser (532 mn) and a gated, intensified charge-coupled device, planar Rayleigh and Raman scattering techniques have been used to visualize the unseeded Mach 0.2 flow density in a 0.3-meter transonic cryogenic wind tunnel. Detection limits are determined for density measurements by using both unseeded Rayleigh and Raman (N2 vibrational) methods. Seeding with C02 improved the Rayleigh flow visualization at temperatures below 150 K. The seeded Rayleigh version was used to demonstrate the observation of transient flow features in a separated boundary layer region, which was excited with an oscillatory jet.
