scholarly journals Feather Vibration as a Stimulus for Sensing Incipient Separation in Falcon Diving Flight

2016 ◽  
Vol 07 (07) ◽  
pp. 411-422 ◽  
Author(s):  
Christoph Brücker ◽  
Daniel Schlegel ◽  
Michael Triep
Keyword(s):  
Incipient Separation

Incipient Separation Near Corners

2018 ◽  
Author(s):  
Anatoly I. Ruban
Keyword(s):  
Corner Point ◽  
Analytic Form ◽  
The Body ◽  
Recirculation Region ◽  
Body Contour ◽  
Concave Corner ◽  
Attached Flow ◽  
Surface Deflection ◽  
Interaction Problem ◽  
Incipient Separation

Chapter 4 analyses the transition from an attached flow to a flow with local recirculation region near a corner point of a body contour. It considers both subsonic and supersonic flow regimes, and shows that the flow near a corner can be studied in the framework of the triple-deck theory. It assumes that the body surface deflection angle is small, and formulates the linearized viscous-inviscid interaction problem. Its solution is found in an analytic form. It also presents the results of the numerical solution of the full nonlinear problem. It shows how, and when, the separation region forms in the boundary layer. In conclusion, it suggests that in the subsonic flow past a concave corner, the solution is not unique.

Development of a laminar boundary layer under conditions of continuous incipient separation

1976 ◽  
Vol 76 (1) ◽  
pp. 55-66 ◽  
Author(s):  
N. Curle
Keyword(s):  
Boundary Layer ◽  
Pressure Distribution ◽  
Laminar Boundary Layer ◽  
Shape Parameter ◽  
Uniform Pressure ◽  
Continuous Change ◽  
Similar Series ◽  
Image Position ◽  
Incipient Separation

SynopsisThis paper, extending the work of Stratford [6] considers a boundary layer with uniform pressure when x < x0, and with the pressure in x > x0 so chosen that the layer is just on the point of separation for all x >x0. The required pressure distribution is shown to beThe displacement and momentum thicknesses are also derived as series in powers of ξ (and log ξ), and the shape parameter H then obtained as a similar series. The continuous change in H from the Blasius value (when ξ = 0) towards the Falkner-Skan [3] separation value is convincingly demonstrated, with the aid of the leading terms of an asymptomatic expansion for large ξ.

Turbulent flows with incipient separation over solid waves

1989 ◽  
Vol 7 (2) ◽  
pp. 88-98 ◽  
Author(s):  
J. D. Kuzan ◽  
T. J. Hanratty ◽  
R. J. Adrian
Keyword(s):  
Turbulent Flows ◽  
Incipient Separation

A note on hypersonic incipient separation.

AIAA Journal ◽  
1967 ◽  
Vol 5 (12) ◽  
pp. 2284-2285 ◽  
Author(s):  
DAVID A. NEEDHAM
Keyword(s):  
Incipient Separation

Hypersonic Flow Separation in Shock Wave Boundary Layer Interactions

1992 ◽  
Author(s):  
A. Hamed ◽  
Ajay Kumar
Keyword(s):  
Boundary Layer ◽  
Shock Wave ◽  
Flow Separation ◽  
Characteristic Length ◽  
Separated Flow ◽  
Surface Cooling ◽  
Flat Plates ◽  
Shock Interactions ◽  
Wave Boundary ◽  
Incipient Separation

This work presents an assessment of the experimental data on separated flow in shock wave turbulent boundary layer interactions at hypersonic and supersonic speeds. The data base consist of selected configurations where the only characteristic length in the interation is the incoming boundary layer thickness. It consists of two dimensional and axisymmetric interactions in compression corners or cylinder-flares, and externally generated oblique shock interactions with boundary layers over flat plates or cylindrical surfaces. The conditions leading to flow separation and the empirical correlations for incipient separation are reviewed. The effects of Mach number, Reynolds number, surface cooling and the methods of detecting separation are discussed.

Incipient separation pressure rise for a Mach 3.8 turbulent boundarylayer.

AIAA Journal ◽  
1973 ◽  
Vol 11 (5) ◽  
pp. 761-763 ◽  
Author(s):  
WILLIAM C. ROSE ◽  
RICHARD J. PAGE ◽  
MORRIS E. CHILDS
Keyword(s):  
Pressure Rise ◽  
Incipient Separation
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