Author: Publisher:
ISBN:
Category :
Languages : en
Pages : 316
Book Description
Experimental Investigation of the Interaction of a Plane, Oblique, Incident-reflecting Shock Wave with a Turbulent Boundary Layer on a Cooled Surface. Volume 3 - Tabulated Data
Experimental Investigation of the Interaction of a Plane, Oblique, Incident-reflecting Shock Wave with a Turbulent Boundary Layer on a Cooled Surface. Volume 2 - Basic Plotted Data
Author: Experimental Investigation of the Interaction of a Plane, Oblique, Incident-reflecting Shock Wave with a Turbulent Boundary Layer on a Cooled Surface. Volume 1 - Test Description and Data Summary
Author: Scientific and Technical Aerospace Reports
Author: Oblique Shock Wave/Turbulent Boundary Layer Interactions in Three Dimensions at Mach 3
Author: B. OskamPublisher:
ISBN:
Category :
Languages : en
Pages : 181
Book Description
The second phase of a detailed experimental investigation has been carried out on the interaction between oblique shock waves and turbulent boundary layers in three dimensions. The present work extends the original region of study of the shock wave interaction area towards the streamwise corner between the shock generator and the test wall. The purpose of this report is to present the experimental data in tabulated form. The tabulations include both surface data such as heat transfer and static pressure as well as detailed flow field surveys of pitot pressure, flow angularity, static pressure and total temperature.
An Experimental Investigation of Shock Wave-turbulent Boundary Layer Interactions with and Without Boundary Layer Suction
Author: C. C. SunPublisher:
ISBN:
Category : Shock waves
Languages : en
Pages : 916
Book Description
Tabulated data from a series of experimental studies of the interaction of a shock wave with a turbulent boundary layer in axisymmetric flow configurations is presented. The studies were conducted at the walls of circular wind tunnels and on the cylindrical centerbody of an annular flow channel. Detailed pitot pressure profiles and wall static pressure profiles upstream of, within and downstream of the interaction region are given. Results are presented for flows at nominal freestream Mach Numbers of 2, 3 and 4. For studies at the tunnel sidewalls, the shock waves were produced by conical shock generators mounted on the centerline of the wind tunnel at zero angle of attack. The annular ring generator was used to produce the shock wave at the centerbody of the annular flow channel. The effects of boundary layer bleed were examined in the investigation. Both bleed rate and bleed location were studied. Most of the bleed studies were conducted with bleed holes drilled normal to the wall surface but the effects of slot suction were also examined. A summary of the principal results and conclusions is given.
Experimental Investigation of the Interaction of an Oblique Shock Wave with a Turbulent Boundary Layer
Author: Amado Arthur TrujilloPublisher:
ISBN:
Category :
Languages : en
Pages : 254
Book Description
Investigation of Laminar and Turbulent Boundary Layers Interacting with Externally Generated Shock Waves
Author: Earl C. WatsonPublisher:
ISBN:
Category : Laminar boundary layer
Languages : en
Pages : 140
Book Description
Laminar and turbulent boundary layer interactions with externally generated shock waves.
NASA SP.
Author: Data on Effects of Incident-reflecting Shocks on the Turbulent Boundary Layer
Author: S. Z. PinckneyPublisher:
ISBN:
Category : Aerodynamics, Hypersonic
Languages : en
Pages : 220
Book Description