scholarly journals Shock-induced separated structures in symmetric corner flows

1995 ◽  
Author(s):  
D D'Ambrosio ◽  
R Marsilio ◽  
M Pandolfi
Keyword(s):  
Corner Flows

scholarly journals Numerical Solutions of Supersonic and Hypersonic Laminar Compression Corner Flows

AIAA Journal ◽  
1976 ◽  
Vol 14 (4) ◽  
pp. 475-481 ◽  
Author(s):  
C.M. Hung ◽  
R.W. MacCormack
Keyword(s):  
Numerical Solutions ◽  
Compression Corner ◽  
Corner Flows

Thin-layer approximation for three-dimensional supersonic corner flows

AIAA Journal ◽  
1980 ◽  
Vol 18 (12) ◽  
pp. 1544-1546 ◽  
Author(s):  
C. M. Hung ◽  
Seth S. Kurasaki
Keyword(s):  
Thin Layer ◽  
Three Dimensional ◽  
Thin Layer Approximation ◽  
Corner Flows

Comparison of Numerical and Experimental “Conical” Flow Fields in Supersonic Corners with Compression and/or Expansion

1977 ◽  
Vol 28 (4) ◽  
pp. 293-306 ◽  
Author(s):  
D A Anderson ◽  
R K Nangia
Keyword(s):  
Flow Field ◽  
Numerical Method ◽  
Three Dimensional ◽  
Solid Surfaces ◽  
Supersonic Stream ◽  
Conical Flow ◽  
Wave Interactions ◽  
Surface Deflection ◽  
Corner Flows ◽  
General Influence

SummaryThe flow field produced by the intersection of two plane solid surfaces in a supersonic stream is a complex interference flow. These flows can be fully compressive, fully expansive or of mixed compression-expansion nature. This paper presents a comparison of the flow field structure in an axial corner obtained experimentally with that predicted numerically by using a shock-capturing finite-difference method. The effect of sweep and surface deflection are evaluated and the general influence of each is presented for the three classes of corner flows. The results of this study show that the numerical method is a valuable aid in understanding the flow structure for simple configurations. In addition confidence in the numerical method is gained for use in solving the more general three-dimensional configurations where the flow is non-conical and several wave interactions may be present.

A Reynolds Stress Model for Turbulent Corner Flows—Part II: Comparisons Between Theory and Experiment

1976 ◽  
Vol 98 (2) ◽  
pp. 269-276 ◽  
Author(s):  
F. B. Gessner ◽  
J. K. Po
Keyword(s):  
Reynolds Stress ◽  
Reynolds Stress Model ◽  
Length Variation ◽  
Stress Model ◽  
Duct Flow ◽  
Rectangular Duct ◽  
Proposed Model ◽  
Alternate Model ◽  
Corner Flows ◽  
Good Agreement

The applicability of the Reynolds stress model developed in Part I to fully developed rectangular duct flow is investigated. Two sets of experimental data are analyzed in order to prescribe a representative mixing length variation and appropriate values for the constants in the model. Predicted Reynolds stress values are in good agreement with their experimental counterparts for both sets of data. These results are compared with predictions referred to an alternate model in order to explain discrepancies observed in a previous study. Possible extensions of the proposed model to increase its flexibility are discussed.

Flow along streamwise corners revisited

2003 ◽  
Vol 476 ◽  
pp. 223-265 ◽  
Author(s):  
A. RIDHA
Keyword(s):  
Boundary Layer ◽  
Flat Plate ◽  
Three Dimensional ◽  
Numerical Results ◽  
Intermediate Layers ◽  
Concave Corner ◽  
Dimensional Boundary ◽  
Streamwise Pressure Gradient ◽  
Corner Flows ◽  
Corner Layer

In this paper we investigate the three-dimensional laminar incompressible steady flow along a corner formed by joining two similar quarter-infinite unswept wedges along a side-edge. We show that a four-region construction of the potential flow arises naturally for this flow problem, the formulation being generally valid for a corner of an arbitrary angle (π−2α), including the limiting cases of semi- and quarter-infinite flat-plate configurations. This construction leads to five distinct three-dimensional boundary-layer regions, whereby both the spanwise length and velocity scales of the blending intermediate layers are O(δ), with Re−1/2 [Lt ] δ [Lt ] 1, Re being a reference Reynolds number supposed to be large. This reveals crucial differences between concave and convex corner flows. For the latter flow regime, the corner-layer motion is shown to be mainly controlled by the secondary flow which effectively reduces to that past sharp wedges with solutions being unique and existing only for favourable streamwise pressure gradients. In this regime, the corner-layer thickness is shown to be O(Re−0.5+α/π/δ2α/π), −½π [les ] α [les ] 0, which is much smaller than O(Re−1/2) for concave corner flows.Crucially, our numerical results show conclusively that, for α ≠ 0, closed streamwise symmetrically disposed vortices are generated inside the intermediate layers, confirming thus the prediction made by Moore (1956) for a rectangular corner, which has so far remained unconfirmed in the literature.For almost planar corners, three-dimensional corner boundary-layer features are shown, as in (Smith 1975), to arise when α ∼ O(1/ln Re). On the other hand, we show that the flow past a quarter-infinite flat plate would be attained when both values of the streamwise pressure gradient and external corner angle (π+2α) become O(1/ln Re) or smaller.Numerical results for all these flow regimes are presented and discussed.

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