Effect of Controlled Surface Roughness on Boundary-layer Transition and Heat Transfer at Mach Numbers of 4.8 and 6.0 PDF Download
Are you looking for read ebook online? Search for your book and save it on your Kindle device, PC, phones or tablets. Download Effect of Controlled Surface Roughness on Boundary-layer Transition and Heat Transfer at Mach Numbers of 4.8 and 6.0 PDF full book. Access full book title Effect of Controlled Surface Roughness on Boundary-layer Transition and Heat Transfer at Mach Numbers of 4.8 and 6.0 by Paul F. Holloway. Download full books in PDF and EPUB format.
Author: Paul F. Holloway
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 54
Get Book Here
Book Description
Author: Paul F. Holloway
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 54
Get Book Here
Book Description
Author: United States. National Aeronautics and Space Administration Scientific and Technical Information Division
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1152
Get Book Here
Book Description
Author: K. R. Czarnecki
Publisher:
ISBN:
Category : Body of revolution
Languages : en
Pages : 30
Get Book Here
Book Description
Author: Eugene Sevigny
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 50
Get Book Here
Book Description
Author: William D. Deveikis
Publisher:
ISBN:
Category : Fluid mechanics
Languages : en
Pages : 30
Get Book Here
Book Description
Author: James C. Dunavant
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 44
Get Book Here
Book Description
Author: James R. Hall
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 34
Get Book Here
Book Description
Author: Albert L. Braslow
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 624
Get Book Here
Book Description
The method has been applied to various types of configurations in several wind-tunnel investigations conducted by the National Advisory Committee for Aeronautics at Mach numbers up to 4, and in all cases the calculated roughness height caused premature boundary-layer transition for the range of test conditions.
Author: A. L. Braslow
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 13
Get Book Here
Book Description
A discussion is presented on the transition phenomena associated with distributed roughness, a correlation of three-dimensional roughness effects at both subsonic and supersonic speeds, and the effect of laminar boundary-layer stability as influenced by heat transfer, pressure gradients, and boundary-layer control on the sensitivity of laminar flow to distributed roughness. Results indicate that the transition-triggering mechanism of three-dimensionaltype surface roughness appears to be the same at supersonic and subsonic speeds. In either case, a Reynolds number based on the height of the roughness and the local flow conditions at the top of the roughness can be used to predict with reasonable accuracy the height of threedimensional roughness required to cause premature transition. Neither the three-dimensional roughness Reynolds number nor the lateral spread of turbulence behind the roughness is changed to any important extent by increasing the laminar boundary-layer stability to theoretically small disturbances. Therefore, for a given stream Mach number and Reynolds number, surface cooling, boundary-layer suction, or a favorable pressure gradient will, in the presence of three-dimensional roughness, promote rather than delay transition. (Author).
Author: Paul F. Holloway
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 52
Get Book Here
Book Description
