Development of Stationary Crossflow Vortices on a Swept Wing

Radeztsky, Ronald H.; Reibert, Mark S.; Saric, William S.

doi:10.1007/978-3-642-79765-1_35

Cited by 19 publications

(30 citation statements)

References 10 publications

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“…Stationary crossflow waves often show evidence of strong nonlinear effects [28][29][30][31][32][33][34][35]. Because the wavefronts are fixed with respect to the model and are nearly aligned with the local potential-flow direction (i.e.…”

Section: (D) Three-dimensional Boundary Layers: Crossflow Wavesmentioning

confidence: 99%

Passive control of transition in three-dimensional boundary layers, with emphasis on discrete roughness elements

Saric

Carpenter

Reed

2011

Phil. Trans. R. Soc. A.

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A brief review of laminar flow control techniques is given and a strategy for achieving laminarization for transonic transport aircraft is discussed. A review of some flight-test results on swept-wing transition is presented. It is also shown that polished leading edges can create large regions of laminar flow because the flight environment is relatively turbulence free and the surface finish reduces the initial amplitude of the stationary crossflow vortex.

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Section: (D) Three-dimensional Boundary Layers: Crossflow Wavesmentioning

confidence: 99%

Passive control of transition in three-dimensional boundary layers, with emphasis on discrete roughness elements

Saric

Carpenter

Reed

2011

Phil. Trans. R. Soc. A.

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“…The reason was attributed to the quick nonlinear saturation of the disturbance. This statement is basically true in the case of the experiment of Radeztsky et al (1994) [1], where the rms amplitude of the disturbance was already 7% of the local inviscid velocity at the edge of the boundary layer at the location x/c = 0.05, where x is the streamwise coordinate, c the cord length, see Fig.1. However, in a boundary layer, one can hardly say saturation in its strict sense, as the Reynolds number keeps changing in the streamwise direction.…”

Section: Introductionmentioning

confidence: 77%

“…Therefore, much attention have been paid for its investigation, both theoretically and experimentally. However, although local linear stability analysis did provide good results for predicting the shape of the crossflow vortices, the growth rate were usually much overpredicted, see for example Radeztsky et al (1994) [1], Reed et al (1996) [2] and Deyhle & Bippes (1996) [3]. The reason was attributed to the quick nonlinear saturation of the disturbance.…”

Section: Introductionmentioning

confidence: 88%

“…The 45 ~ swept wing cross-section, designated as NLF (2)-0415, and the basic flow profile on the upper surface was kindly provided by Professor Saric (private communication), and the basic flow profile was obtained by numerical computations tailored to the experiment of Radeztsky et al [1] , including a slight adjustment of the angle of attack to make the pressure coefficient almost totally in agreement with the experiment. Figure 2 shows the typical flow profile in the streamwise direction and crossflow direction at the location where x/c = 0.4.…”

Section: The Governing Equations and Factors Influencing The Growth Ratementioning

confidence: 99%

“…In the experiment, the disturbance was introduced by putting roughness elements near the leading edge. For details of the experiment, please refer to Radeztsky et al (1994) [11. We chose a coordinate system such that the z axis is parallel to the leading edge of the wing, s perpendicular to z and tangent to the surface, and r/ orthogonal to both z and s. Let U + u be the instantaneous velocity, where U = {U,0, W} w is the laminar flow, u ~ = {u', v t, w'} w the disturbance.…”

Section: The Governing Equations and Factors Influencing The Growth Ratementioning

confidence: 99%

See 2 more Smart Citations

A theoretical investigation of the development of stationary crossflow vortices in the boundary layer on a swept wing

Luo

Zhou

1998

Acta Mech Sinica

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ABSTRACT:Crossflow instability plays very important role in the transition of the boundary layer on a swept wing, typical in the engineering applications. Experiments revealed that the linear stability theory well predicted the form of the crossflow vortices, but usually much overpredicted their growth rate. Using nonlinear theory of hydrodynamic stability, combined with some other considerations, we were able to obtain the growth rate in good agreement with experimental observations.

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Görtler vortices promoted by wall roughness

Bottaro

Zebib

1997

Fluid Dyn. Res.

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Numerical experiments are conducted to investigate spatially developing Grrtler vortices and the way in which wall roughness promotes their formation and growth. Several different types of walls are examined and their relative merits as vortex promoters assessed. The only disturbances of the flow are due to the rough wall; hence, at each downstream station the local field feels (1) the upstream flow distribution (produced by the upstream wall conditions) and ( 2) the local forcing at the wall. Rapid vortex formation and growth, like in the case of ribleted walls, can be qualitatively explained by the positive combination of these two effects; when the two influences on the local flow field compete, e.g. for randomly distributed wall roughness, the equations with the boundary conditions filter the disturbances over some streamwise length, function of the roughness amplitude, to create coherent patches of vorticity out of the random noise.These patches can then be amplified by the instability mechanism. If a thin rough strip is aligned along the span of an otherwise smooth wall to trip the boundary layer, the filtering region is shorter and growth of the vortices starts earlier. Also for the case of an isolated three-dimensional hump a rapid disturbance amplification is produced, but in this case the vortices remain confined and a very slow spanwise spreading of the perturbation occurs. In all naturally developing cases, where no specific wavelengths are explicitly favored, the average spanwise wavelengths computed are very close to those of largest growth from the linear stability theory.

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Development of Stationary Crossflow Vortices on a Swept Wing

Cited by 19 publications

References 10 publications

Passive control of transition in three-dimensional boundary layers, with emphasis on discrete roughness elements

Passive control of transition in three-dimensional boundary layers, with emphasis on discrete roughness elements

A theoretical investigation of the development of stationary crossflow vortices in the boundary layer on a swept wing

Görtler vortices promoted by wall roughness

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