Author: M. L. Riethmuller
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 96
Book Description
A Parametric Study of Adiabatic Laminar Boundary Layer-shock Wave Interactions by the Method of Lees-Reeves-Klineberg
Author: M. L. Riethmuller
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 96
Book Description
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 96
Book Description
The Calculation of Adiabatic Laminar Boundary Layer Shock Wave Interactions in Axi-symmetric Flow
Author: Harry P. Horton
Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 74
Book Description
Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 74
Book Description
Scientific and Technical Aerospace Reports
A Theoretical Study of Wall Cooling Effects Upon Shock Wave-laminar Boundary Layer Interaction by the Method of Lees-reeves-klineberg
Author: Bernard G. Gautier
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 100
Book Description
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 100
Book Description
Shock Wave - Turbulent Boundary Layer Interaction in High Speed Flow
Author: Michael S. Holden
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 188
Book Description
Publisher:
ISBN:
Category : Aerodynamic heating
Languages : en
Pages : 188
Book Description
Laminar and Turbulent Separation Including Three-dimensional Effects
Author: Von Karman Institute for Fluid Dynamics
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 254
Book Description
Publisher:
ISBN:
Category : Aerodynamics
Languages : en
Pages : 254
Book Description
The Aeronautical Journal
Influence of Cross Flow on Two Dimensional Separation
Author: Roger LeBlanc
Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 56
Book Description
The report is a review of some of the problems associated with the design of a rotating axi-symmetric body to study the effect of cross flow on two dimensional separation. A hollow cylinder flare model with 8 in. diameter was designed to rotate up to 5,000 r.p.m. in the 16 in. x 16 in. test section of the VKI continuous supersonic wind tunnel S-1 at a free stream Mach number of 2.25. Problems related to the static pressure measuring equipment, the optimum model configuration, the model driving mechanism and the model vibrations are discussed. (Author).
Publisher:
ISBN:
Category : Fluid dynamics
Languages : en
Pages : 56
Book Description
The report is a review of some of the problems associated with the design of a rotating axi-symmetric body to study the effect of cross flow on two dimensional separation. A hollow cylinder flare model with 8 in. diameter was designed to rotate up to 5,000 r.p.m. in the 16 in. x 16 in. test section of the VKI continuous supersonic wind tunnel S-1 at a free stream Mach number of 2.25. Problems related to the static pressure measuring equipment, the optimum model configuration, the model driving mechanism and the model vibrations are discussed. (Author).
Aeronautical Engineering
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 976
Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 976
Book Description
A selection of annotated references to unclassified reports and journal articles that were introduced into the NASA scientific and technical information system and announced in Scientific and technical aerospace reports (STAR) and International aerospace abstracts (IAA).