The results of wind-tunnel experiments and laser vapour screen flow observation proved the configuration to be effective. An unsteady region during the transition of symmetric vortices to asymmetric ones was discovered.

Effectiveness of the fast swinging micro tip strake technique for controlling forebody vortex asymmetry at high angles of attack has been investigated and de veloped in low speed wind tunnel experiments on a slender body of revolution wi th pointed nose configuration.

For steady asymmetric vortical flow, study shows that the side force on after cylinder induced by asymmetric nose vortices is significantly weakened, because of boundary layer separation on after body is blocked by section of wingbody combination, and also shows that the outplane force on wingbody combination with "○"configuration is larger than those on body alone.

Influence of nose perturbations on behaviors of asymmetric vortices over slender body

The influence of nose perturbations on the behaviors of asymmetric vortices over a slender body with a three-caliber ogive nose is studied in this paper.

The effect of the perturbation axial location on asymmetric vortices is the strongest if its location is near the model apex.

Various types of perturbation do not change the perturbation effect on the behaviors of bistable asymmetric vortices.

Asymmetric vortices flow over slender body and its active control at high angle of attack

Static properties of asymmetric vortex-like domain walls in magnetically uniaxial thick films

It is established that the asymmetric vortex-like domain walls are the most universal wall structures in the films under consideration.

In the turning region, a pair of Dean vortices shown in the stationary case transform into one large asymmetric vortex cell, and subsequently heat/mass transfer and pressure drop characteristics also change.

The flow is quite sensitive to directional perturbations, with even slight inclinations of the jet with respect to the counterflow resulting in regular asymmetric vortex shedding and a decreased mean downstream extent.

Numerical investigation of the mechanism of asymmetric vortex flows

Asymmetric vortices flow over slender body and its active control at high angle of attack

The studies of asymmetric vortices flow over slender body and its active control at high angles of attack have significant importance for both academic field and engineering area.

Flow pattern visualizations and surface pressure measurements on a slender body witb two different elliptical cross-section noses were conducted at sideslip and high angle of attack condition, under which the body generates an asymmetric vortex system. The mechanism of how a flattened nose shape can contribute the directional stability to the slender body fitted with various noses at high angle of attack has been investigated and revealed by analyzing and comparing the flow patterns, the cross-sectional pressure...

Flow pattern visualizations and surface pressure measurements on a slender body witb two different elliptical cross-section noses were conducted at sideslip and high angle of attack condition, under which the body generates an asymmetric vortex system. The mechanism of how a flattened nose shape can contribute the directional stability to the slender body fitted with various noses at high angle of attack has been investigated and revealed by analyzing and comparing the flow patterns, the cross-sectional pressure and the side force distributions along axis of bodies.

This paper studies the phenomenon of off-surface forces and moments due to asymmetric vortices on a cylindrical body with ogive nose at high angles of attack in subsonic and transonic flows.Methods to allev'iate those undesirable forces and moments are discussed.An appropriate nose configuration was designed and tested.The results of wind-tunnel experiments and laser vapour screen flow observation proved the configuration to be effective.An unsteady region during the transition of symmetric vortices to asymmetric...

This paper studies the phenomenon of off-surface forces and moments due to asymmetric vortices on a cylindrical body with ogive nose at high angles of attack in subsonic and transonic flows.Methods to allev'iate those undesirable forces and moments are discussed.An appropriate nose configuration was designed and tested.The results of wind-tunnel experiments and laser vapour screen flow observation proved the configuration to be effective.An unsteady region during the transition of symmetric vortices to asymmetric ones was discovered.

The viscous flow around a rectangular cylinder is simulated by solving the two dimensional compressible Navier-Stokes equations. The partial differential equations are approximated by difference methods such as special chosen Jacobian matrix splitting technique and approximate factorization. The scheme has second order accuracy in space and time. The Mach number Ma =0.3 and the Reynold number Re = 20000 are used in the computation. The unsteady Karman vortex separation and asymmetry of pair of vortices can be...

The viscous flow around a rectangular cylinder is simulated by solving the two dimensional compressible Navier-Stokes equations. The partial differential equations are approximated by difference methods such as special chosen Jacobian matrix splitting technique and approximate factorization. The scheme has second order accuracy in space and time. The Mach number Ma =0.3 and the Reynold number Re = 20000 are used in the computation. The unsteady Karman vortex separation and asymmetry of pair of vortices can be seen clearly from the computed results, The old vortices are moved downstream and the new ones are generated from the corner of the cylinder. The influence of compressibility on vortex formation is considered. The critical Reynold number Rec is increased with the Mach number increased.