Author: Aeronautical Research CouncilPublisher:
ISBN:
Category :
Languages : en
Pages : 47
Book Description
An Experimental Investigation of the Interaction Between a Forward-facing Step and a Laminar Boundary Layer in Supersonic, Lowdensity Flow
Author: Aeronautical Research CouncilPublisher:
ISBN:
Category :
Languages : en
Pages : 47
Book Description
An Experimental Investigation of the Interaction Between a Forward-facing Step and a Laminar Boundary Layer in Supersonic, Low-density Flow
Author: E. W. E. RogersPublisher:
ISBN:
Category : Air flow
Languages : en
Pages : 46
Book Description
An Experimental Investigation of the Interaction Between a Forward-facing Step and a Laminar Boundary Layer in Supersonic Low-density Flow
Author: E. W. E. RogersNASA Technical Note
Author: Technical Abstract Bulletin
Author: Scientific and Technical Aerospace Reports
Author: Advances in Heat Transfer
Author: Publisher: Academic Press
ISBN: 0080575609
Category : Science
Languages : en
Pages : 591
Book Description
Advances in Heat Transfer
Wedge-induced Laminar-boundary-layer Separation on a Flat Plate in Low-density, Hypervelocity Flow
Author: John Benjamin AndersPublisher:
ISBN:
Category : Boundary layer control
Languages : en
Pages : 36
Book Description
An experimental investigation of the turbulent boundary layer behind a forward facing step in supersonic flow
Author: Dave Robert MoorePublisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 106
Book Description
The report presents the results of an experimental study of the effect of a disturbance, produced by a forward facing step, on the turbulent boundary layer in compressible flow. Boundary layer total pressure surveys and direct skin friction measurements were made at six stations on each of two test surfaces. One surface was smooth and the other surface had an 0.080-inch forward facing step. The test stations were all located downstream of the step, the height of which was approximately one-half the smooth surface boundary layer thickness. Data were obtained at Mach Numbers of 2.0, 2.5, 3.0, and 3.5 and the test Reynolds Numbers, based on momentum thickness, ranged from 8,000 to 10,000 approximately. The results of this investigation indicate that the effect of the disturbance, produced by the step on the 'law of the wall' and 'velocity defect law' profiles appears to be negligible from a point approximately 10 flat plate boundary layer thicknesses downstream from the step. (Author).
Theoretical Face Pressure and Drag Characteristics of Forward-facing Steps in Supersonic Turbulent Boundary Layers
Author: D. K. PatelPublisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 68
Book Description