Photographic Evidence of Streamwise Arrays of Vortices in Boundary-layer Flow PDF Download
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Author: Edward J. Hopkins
Publisher:
ISBN:
Category : Boundary layer control
Languages : en
Pages : 28
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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: Edward J. Hopkins
Publisher:
ISBN:
Category : Boundary layer control
Languages : en
Pages : 24
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 412
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Book Description
Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : Government publications
Languages : en
Pages : 1812
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Author: United States. Superintendent of Documents
Publisher:
ISBN:
Category : United States
Languages : en
Pages : 1366
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Author: United States. National Aeronautics and Space Administration
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Wen Jei Yang
Publisher: Routledge
ISBN: 1351442619
Category : Technology & Engineering
Languages : en
Pages : 723
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Book Description
With contributions from some of the world's leading experts, the second edition of this classic reference compiles all major techniques of flow visualization and demonstrates their applications in all fields of science and technology. A new chapter has been added that covers flow visualization applications in large wide tunnels for airplane and automobile testing. Several important examples of applications are included. A second new chapter details the use of infrared (IR) cameras for detecting and observing the boundary layer transition in industrial wind tunnels and flight testing of commercial transport airplanes. A final new chapter has been added on multiphase flow and pulsed-light velocimetry.
Author: Jean J. Ginoux
Publisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 40
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Book Description
An experimental investigation was made in various supersonic and hypersonic wind tunnels to determine the effect of Mach number on the existence of streamwise vortices in the reattachment region of the flow over twodimensional backward facing steps. It was found that the phenomenon previously observed at M = 2.21 remained unchanged over a Mach number range of 1.5 to 7.0. The ratio of the wave length of the vortices to the boundary layer thickness at separation varied slightly with free stream Mach number, with a maximum at about M = 3. (Author).
Author: Bruce James Wendt
Publisher:
ISBN:
Category :
Languages : en
Pages : 616
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Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 450
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