Leading-Edge Separation of Laminar Boundary Layers in Supersonic Flow

1961 ◽  
Vol 28 (12) ◽  
pp. 957-961 ◽  
Author(s):  
W. B. BROWER
Keyword(s):  
Supersonic Flow ◽  
Boundary Layers ◽  
Leading Edge ◽  
Laminar Boundary Layers ◽  
Edge Separation

The supersonic flow past a leading edge separation bubble

1959 ◽  
Vol 5 (3) ◽  
pp. 445-459 ◽  
Author(s):  
A. W. Sharp
Keyword(s):  
Supersonic Flow ◽  
Wave Equations ◽  
Separation Bubble ◽  
Leading Edge ◽  
Plate Surface ◽  
Sonic Line ◽  
Base Points ◽  
Bow Wave ◽  
Edge Separation ◽  
Good Agreement

The supersonic flow field outside a leading edge separation bubble has been computed in detail by a special application of the method of characteristics. Experimental observations on a two-dimensional square-nosed flat plate at M = 1·96 formed the initial data, and base points were established on the plate surface. Computations proceeded outwards and upstream to the sonic line and bow wave, the bow wave entropy gradient being taken into account. The shape of the sonic line was found to be very sensitive to the conditions along the plate surface. Streamlines and iso-Mach lines have been interpolated and are presented. Good agreement was found at the intersection of the network and the bow wave between computed values and those given directly by the shock wave equations. A comparison has been made with interferometric results from France.

The Measurement of Boundary Layers on a Compressor Blade in Cascade: Part 2—Suction Surface Boundary Layers

1988 ◽  
Vol 110 (1) ◽  
pp. 138-145 ◽  
Author(s):  
S. Deutsch ◽  
W. C. Zierke
Keyword(s):  
Boundary Layers ◽  
Separation Bubble ◽  
Incidence Angle ◽  
Outer Region ◽  
Leading Edge ◽  
Compressor Blade ◽  
Surface Boundary ◽  
Suction Surface ◽  
Circular Arc ◽  
Edge Separation

Using the facility described in Part 1 [29], eleven detailed velocity and turbulence intensity profiles are obtained on the suction surface of a double circular arc blade in cascade. At the measured incidence angle of 5 deg, transition through a leading edge separation bubble occurs before 2.6 percent chord. A continuing recovery from this leading edge separation is apparent in the measured boundary layer profiles at 2.6 and 7.6 percent chord. Recovery appears to be complete by 12.7 percent chord. The data then illustrate the evolution of the nonequilibrium turbulent boundary layers as they approach a second region of separation. Following the criteria established by Simpson et al. [1], we find that intermittent separation occurs near 60 percent chord while detachment occurs at 84.2 percent chord. Comparison between the measured profiles and the sublimation visualization studies indicates that the flow visualization is signaling the location of incipient detachment (1 percent instantaneous backflow). Measured profiles are also considered in light of similarity techniques for boundary layers approaching separation. Outer region similarity is shown to vanish for profiles downstream of detachment.

NEW IMAGINARY-VALUED SIMILARITY SOLUTIONS FOR LAMINAR BOUNDARY LAYERS WITH A SPRAY

2009 ◽  
Vol 19 (12) ◽  
pp. 1105-1111
Author(s):  
Ro'ee Z. Orland ◽  
David Katoshevski ◽  
D. M. Broday
Keyword(s):  
Boundary Layers ◽  
Similarity Solutions ◽  
Laminar Boundary Layers

scholarly journals On a Simple Method for Calculating Laminar Boundary Layers

1954 ◽  
Vol 5 (1) ◽  
pp. 25-38 ◽  
Author(s):  
K. E. G. Wieghardt
Keyword(s):  
Boundary Layers ◽  
Parametric Method ◽  
Symmetric Flow ◽  
Numerical Constant ◽  
Simple Method ◽  
Plane Flow ◽  
Laminar Boundary Layers ◽  
Energy Equations

SummaryA simple one parametric method, due to A. Walz and based on the momentum and energy equations, for calculating approximately laminar boundary layers is extended to cover axi-symmetric flow as well as plane flow. The necessary computing work is reduced a little.Another known method which requires still less computing work is also extended for axi-symmetric flow and, with the amendment of a numerical constant, proves adequate for practical purposes.

Laminar boundary layers behind detonation waves

1983 ◽  
Vol 387 (1793) ◽  
pp. 331-349 ◽  
Keyword(s):  
Heat Transfer ◽  
Boundary Layer ◽  
Boundary Layers ◽  
Flow Analysis ◽  
Time Dependent ◽  
Detonation Waves ◽  
Planar Geometry ◽  
Laminar Boundary Layers ◽  
Spherical Detonation ◽  
Layer Flow

New solutions are presented for non-stationary boundary layers induced by planar, cylindrical and spherical Chapman-Jouguet (C-J) detonation waves. The numerical results show that the Prandtl number ( Pr ) has a very significant influence on the boundary-layer-flow structure. A comparison with available time-dependent heat-transfer measurements in a planar geometry in a 2H 2 + O 2 mixture shows much better agreement with the present analysis than has been obtained previously by others. This lends confidence to the new results on boundary layers induced by cylindrical and spherical detonation waves. Only the spherical-flow analysis is given here in detail for brevity.

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