Unsteady Reattachment Of Supersonic Flow Past A Backward Facing Step
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SUPERSONIC FLOW SEPARATION ON A BACKWARD FACING STEP.
| Author | : |
| Publisher | : |
| Total Pages | : 42 |
| Release | : 1966 |
| Genre | : |
| ISBN | : |
The paper describes an experimental survey of flow separation on backward facing steps having different heights at a Mach number of 2.4. Reattachment and critical points are found for three regimes, laminar, transitional, and turbulent. Reattachment occurs at a point where the pressure is 35% of the free stream value for turbulent flow, and 60% of this value in the laminar case. The length of the free shear layer is found to be one-half that of the separating streamline, a result which emphasizes the importance of the reattachment region. The flow downstream of the critical point is found to be relatively independent of the base flow. Disturbances in the spanwise direction are always observed in laminar flow but do not affect the base pressure.
Supersonic Separated Flow Downstream of a Backward Facing Step
| Author | : Donald R. Crawford |
| Publisher | : |
| Total Pages | : 166 |
| Release | : 1967 |
| Genre | : |
| ISBN | : |
The method of integral relations is applied to the study of the viscous separated flow field downstream of a backward facing step in laminar supersonic flow. The boundary layer equations are reduced to a set of coupled ordinary differential equations in a formulation which incorporates a two parameter velocity profile. The neighborhood of the corner and the reattachment point are examined in detail, taking into account the proper interaction between the viscous and inviscid flow. The complete flow field in these regions is found from the analyses of the limiting forms of the equations. In particular, it is found that the pressure gradient and thickness of the boundary layer at the reattachment point are related and cannot be arbitrarily specified. (Author).
Separation and Reattachment of Supersonic Turbulent Boundary Layer Behind Down Stream Facing Steps and Over Cavities
| Author | : G. J. Thomke |
| Publisher | : |
| Total Pages | : 180 |
| Release | : 1964 |
| Genre | : Aerodynamics, Supersonic |
| ISBN | : |
Surface pressure measurements were obtained for the flow regimes created when a turbulent boundary layer in supersonic flow separates over the classical downstream-facing step and over a cavity. The experiments were conducted in the Mach number range 2.0 to 4.0 on a model having a ducted, one-foot diameter, axisymmetric body. The model provided step heights of 0.250, 1.020, and 1.675 inches, cavity lengths of 0.837 and 1.675 inches, and a cavity depth of 1.675 inches. The recompression shoulder of the cavity had either a square or a rounded shape. In general, the pressure rise at reattachment is found to be in good agreement with Korst's theory. The shape and scale of the reattachment pressure distribution are influenced considerably by Mach number. Reattachment occurs at a point where the pressure rise is about 50% complete. A point of flow reversal is found to be located upstream of the reattachment point. (Author).
Turbulent Flow Reattachment
| Author | : John K. Eaton |
| Publisher | : |
| Total Pages | : 184 |
| Release | : 1980 |
| Genre | : Boundary layer |
| ISBN | : |
