Influence of blowing on the characteristics of the nonstationary boundary layer on an oscillating wedge in a supersonic stream

1981 ◽  
Vol 16 (1) ◽  
pp. 139-142 ◽  
Author(s):  
E. S. Kornienko ◽  
V. N. Shmanenkov
Keyword(s):  
Boundary Layer ◽  
Supersonic Stream ◽  
Nonstationary Boundary

Nonstationary Boundary Layer of a Fluid with the Ladyzhenskaya Rheological Law

2020 ◽  
Vol 249 (6) ◽  
pp. 850-863
Author(s):  
R. R. Bulatova ◽  
V. N. Samokhin ◽  
G. A. Chechkin
Keyword(s):  
Boundary Layer ◽  
Nonstationary Boundary

Flow behind the boundary layer separation point in a supersonic stream

1973 ◽  
Vol 6 (3) ◽  
pp. 378-384 ◽  
Author(s):  
V. Ya. Neiland
Keyword(s):  
Boundary Layer ◽  
Boundary Layer Separation ◽  
Separation Point ◽  
Supersonic Stream ◽  
Layer Separation

Nonstationary Boundary Layer

2018 ◽  
pp. 153-264
Author(s):  
O. A. Oleinik ◽  
V. N. Samokhin
Keyword(s):  
Boundary Layer ◽  
Nonstationary Boundary

The Effect of Sting Supports on the Base Pressure of a Blunt-Based Body in a Supersonic Stream

1955 ◽  
Vol 6 (3) ◽  
pp. 221-229 ◽  
Author(s):  
I. S. Donaldson
Keyword(s):  
Boundary Layer ◽  
Pressure Coefficient ◽  
Diameter Ratio ◽  
Base Pressure ◽  
Supersonic Stream ◽  
Axially Symmetric ◽  
Nozzle Throat ◽  
Base Diameter ◽  
The Difference ◽  
Made In

SummaryExperiments have been made to find the effect of the ratio of sting to base diameter on the base pressure of an axially symmetric body at zero incidence in a supersonic stream. The Mach number of the flow was 1·994 and the model boundary layer was turbulent. The model used was a one inch diameter circular cylinder without boat-tailing. It passed through and was supported upstream of the nozzle throat. This method of support allowed measurements to be made in the important (and hitherto unexplored) case of zero sting diameter.As the sting to base diameter ratio was increased from 0 to 0·85, the base pressure decreased. The minimum value reached was approximately 0·8 of the value it would have at the base of a two-dimensional body with a similar ratio of boundary layer thickness to base height. The base pressure coefficient rose rapidly to zero as the ratio was further increased to unity.Under the conditions of the experiments, with a sting to base diameter ratio of 0·4 the base pressure coefficient differed from that without a sting by approximately ten per cent. With the more modest ratio of 0·2, the difference was approximately three per cent.

Some Experiments on the Interaction of Shock Waves With Boundary Layers on a Flat Plate

1950 ◽  
Vol 17 (2) ◽  
pp. 126-131
Author(s):  
F. W. Barry ◽  
A. H. Shapiro ◽  
E. P. Neumann
Keyword(s):  
Boundary Layer ◽  
Flat Plate ◽  
Boundary Layers ◽  
High Speed ◽  
Incident Shock ◽  
Supersonic Stream ◽  
Turbulent Layer ◽  
Number Range ◽  
Air Stream ◽  
Interaction Of Shock Waves

Abstract Experimental results are presented in the form of schlieren and interferometer photographs showing the interaction of oblique shocks with laminar and turbulent boundary layers on a flat plate in a supersonic stream. The effects of variations in shock intensity and boundary-layer thickness were studied through a Mach number range of 2.0 to 2.5. A greater variety of shock boundary-layer interactions was discovered than had hitherto been suspected. The nature of the interaction was found not to be solely dependent upon whether the boundary layer is laminar or turbulent. A laminar layer proved to be more greatly affected by an incident oblique shock than a turbulent layer. With relatively intense shocks the boundary layer was influenced far upstream of the point of incidence. Injection of a high-speed air stream into a turbulent boundary layer altered significantly the manner of reflection of an incident shock.

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