B. Yu. Zanin

Vortex structure of separated flows on model wings at low freestream velocities

Flow past model wings is experimentally investigated in a subsonic wind tunnel at large angles of attack at which the laminar boundary layer separates near the leading edge of the wing (flow stall). The object of the study was the flow structure within the separation zone. The carbon-oil visualization of surface streamlines used in the experiments showed that in the separation zone there exist one or more pairs of large-scale vortices rotating in the wing plane. Certain general properties of the vortex structures in the separation zone are found to exist, whereas the flow patterns may differ depending on the model aspect ratio, the yaw angle, and other factors.

Global response of laminar flow separation to local flow perturbations (review)

In the present paper, we summarize our experimental data on flow separation control on wings at low subsonic velocities. The focus is on the reduction of the separation region by stationary and nonstationary controlled flow perturbations. Wind-tunnel data obtained for test models of different aspect ratios prove that the entire separated flow can be modified by forcing its narrow parts much smaller in size than the transverse extent of the separation region. Such an approach to flow control at laminar separation comes from non-local interaction of the large-scale flow structure with spatially concentrated disturbances.

Response of axisymmetric separated flow to its spatially localized perturbation

The flow past an axisymmetric body with laminar boundary-layer separation in a low-velocity air stream has been studied. The hot-wire technique was employed to identify the variation of velocity field induced by a local stationary perturbation of separation region at the stern of the experimental model. A large-scale influence upon the near-wall flow due to a cylinder roughness element provided on the model surface was observed. The obtained data substantiate the possibility of controlling the laminar boundary-layer separation on an axisymmetric body using a local external forcing.

Experimental and theoretical investigation of boundary layer perturbations on a low-aspect-ratio wing

Laminar-turbulent transition in a boundary layer of low-aspect-ratio wing was investigated. Experiments clarifying the flow structure, its mean and oscillatory characteristics were carried out accompanied by linear stability analysis of the wind tunnel data on the laminar flow velocity profiles. Theoretical results obtained in a parallel flow approximation are in a good agreement with the experimental data on disturbances evolution at the initial stage of transition to turbulence.

Flow instability in the zone of laminar axisymmetric boundary layer separation

The stability of flow with laminar boundary layer separation from a body of revolution aligned with an incompressible gas stream is investigated in a wind tunnel. In several experimental regimes with respect to the Reynolds number hot-wire anemometry is used to determine the main parameters of disturbances which grow behind the separation line, thus initiating transition to the turbulent flow state. The relations between the frequencies, the spatial growth rates of the most “hazardous” disturbances, and the integral characteristics of velocity profiles obtained in the study are in good agreement with the analogous data for plane separation flows.

Alteration of separated-flow structure achieved through a local action

Results of an experimental study of a subsonic flow past a straight-wing model installed at fixed angle of attack in hysteresis range of flow velocity are reported. It was shown that, at the same angle of attack and at one and the same flow velocity, flows of two types are possible on the upper surface of the model, leading-edge flow stall and re-attached flow with laminar-turbulent transition in the vicinity of the leading edge. It was found that the wing flow could be transformed from stalled to re-attached one with the help of a local influence applied at one point on the model inside the stall zone. Visualization data for both flows, hot-wire anemometer measurements of flow velocity, and measurements of the amplitude and frequency spectra of flow pulsations in both flows, are reported.

Development of laminar-separating-flow perturbations on a wavy wing

The development of velocity perturbations at laminar boundary-layer separation from a wing with wavy surface has been examined. Experiments were carried out to identify flow features displayed by the spatially periodic flow structure. An analysis of the linear stability of measured velocity profiles is performed. As a result of the analysis, the influence of surface waviness on the frequency range and growth rates of instability waves was investigated, with a good agreement between calculated and experimental data.

Transformation of wing boundary layer in the filament wake

Results of an experimental study of the air flow past a straight-wing model in a low-turbulence wind tunnel are reported. The influence of a turbulent wake due to a thin filament on the structure of boundary layer on the model surface was examined. Flow visualization in boundary layer, hot-wire measurements of flow velocity, and also measurements of the amplitude and frequency spectra of flow pulsations, were performed. The wake substantially modified the boundary layer flow pattern: the separation bubble disappeared from the flow, and the formation of longitudinal structures was observed.

Stability of the laminar flow on a body of revolution at incidence

An asymmetric incompressible gas flow past a body of revolution was studied in a subsonic wind tunnel. Characteristics of the velocity field at the stern of the experimental model, where a laminar boundary-layer separation and concomitant destabilization of the flow occur under axisymmetric conditions, were determined. Declination of the axis of symmetry of the body within several angular degrees results in a radical change of the time-average velocity field, the amplitude distribution of growing hydrodynamic disturbances, and their spectral distribution.

Control of Flow Separation from a Model Wing at Low Reynolds Numbers

The results of an experimental investigation of the structure of the flow separated from the model of a straight wing with point sources of disturbances (bulges) made on its surface are presented. The variations in the three-dimensional flow pattern are analyzed as functions of the bulge shapes and positions. It is found that the flow can be controlled by means of mounting the bulges downstream of the separation line, in the return flow region, since in this case they hinder large-scale vortex formation in the separation zone. The results obtained show that there is an intimate connection between the vortices and the separation zone as a whole. Impeding the vortex structure formation can result in considerable variations in the separation zone structure, up to its complete disappearance.