Laminar Separation in Supersonic Flow with Emphasis on Three-dimensional Perturbations at Reattachment PDF Download
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Author: Jean J. Ginoux
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 774
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Book Description
Author: Jean J. Ginoux
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 774
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Book Description
Author: Jean J. Ginoux
Publisher:
ISBN:
Category :
Languages : en
Pages : 1
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Book Description
A study of three-dimensional flow perturbations in laminar supersonic flows was made on flat plates with sweptback leading edges and in the reattachment region of the flow over flat plates with backward-facing steps. It was shown that a cross-flow existed in the boundary layer on flat plates with supersonic sweptback leading edges of small bluntness, which increased in magnitude from the centerline towards the sides of the models. In separated flows, only an extremely small amount of cross-flow was needed to destabilize the flow and to create regular spanwise variations in total pressure. Larger cross-flows, controlled by a systematic variation of the angle of sweep either of the leading edge or of the edge of the step, had no further effect. Detailed surveys made in a reattaching laminar supersonic flow with a static probe showed that the three-dimensional perturbations that existed in the boundary layer were formed by two layers of equidistant contra-rotating streamwise vortices: one located near the wall and a second one near the outer edge of the boundary layer. (Author).
Author: Jean J. Ginoux
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 18
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Book Description
The reattachment region of a laminar boundary layer after separation has been investigated at a Mach number of 2.16. Two-dimensional compression corners and backward or forward facing step models were used. The case of interaction between a shock wave and a laminar boundary layer was also considered. Surface flow was observed by a sublimation technique and detailed span-wise surveys were made in the reattachment region of the flow with total-head probes. Strong, regular and repeatable span-wise perturbations were observed in the boundary layer; these could not be explained by irregularities either in the air flow upstream of the models or in the models themselves. It was found in all cases that street-like flow perturbations existedup to the point where transition occurred. A systematic investigation was made on backward facing steps in order to find out the effects of step height and boundary-layer thickness on the wave length of the flow perturbations. (Author).
Author: United States. Air Force. Office of Scientific Research
Publisher:
ISBN:
Category : Research
Languages : en
Pages : 940
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Author:
Publisher:
ISBN:
Category : Mechanics, Applied
Languages : en
Pages : 686
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Author: Jean J. Ginoux
Publisher:
ISBN:
Category : Aerodynamics, Supersonic
Languages : en
Pages : 1
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Book Description
In supersonic tunnel tests with a two-dimensional backward-facing step model, span-wise perturbations were found in the reattachment region. Studies were made using the same and other similar models. In these later studies, the same three-dimensional perturbations were detected, into the full thickness of the boundary-layer, after reattachment, both in turbulent and laminar regions of the flow. Their amplitude was a maximum in the transition region. Using a model with a much improved accuracy of manufacture, notably at the leading-edge, it was found that the amplitude of the perturbations was greatly reduced, roughly in proportion to the size of the irregularities of manufacture of the leadingedge itself. It is concluded that the phenomenon is essentially one of instability in the twodimensional flow, the main triggering action arising from small irregularities in the leading edge.
Author: W. D. Bachalo
Publisher:
ISBN:
Category : Boundary layer
Languages : en
Pages : 174
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Author:
Publisher:
ISBN:
Category : Science
Languages : en
Pages : 284
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Author: National Aeronautics and Space Adm Nasa
Publisher: Independently Published
ISBN: 9781731300218
Category : Science
Languages : en
Pages : 138
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Book Description
The theory, formulation, and solution of three-dimensional, compressible attached laminar flows, applied to swept wings in subsonic or supersonic flow are discussed. Several new features and modifications to an earlier general procedure described in NASA CR 4269, Jan. 1990 are incorporated. Details of interfacing the boundary-layer computation with solution of the inviscid Euler equations are discussed. A description of the computer program, complete with user's manual and example cases, is also included. Comparison of solutions with Navier-Stokes computations with or without boundary-layer suction is given. Output of solution profiles and derivatives required in boundary-layer stability analysis is provided. Iyer, Venkit Unspecified Center BOUNDARY LAYER STABILITY; COMPRESSIBLE FLOW; COMPUTATIONAL FLUID DYNAMICS; INVISCID FLOW; LAMINAR BOUNDARY LAYER; SWEPT WINGS; THREE DIMENSIONAL FLOW; EULER EQUATIONS OF MOTION; NAVIER-STOKES EQUATION; SUBSONIC FLOW; SUPERSONIC FLOW; USER MANUALS (COMPUTER PROGRAMS)...
Author:
Publisher:
ISBN:
Category : Aeronautics
Languages : en
Pages : 1064
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