By rolling up the surfaces of discontinuity originating from the leading edge of delta wings, free vortex cores are formed above the wing. In case of greater angles of incidence, the flow in these vortex cores shows an instability which abruptly produces strong turbulence. In the present paper an explanation is given of this instability being a "frictionless instability" of the vortex core flow by increasing helical interference vortices. The occurring vortex core flows are calculated and investigated for stability by means of a stability criterion concerning flows with helical streamlines given by H. Ludwieg
Time-resolved stereoscopic particle image velocimetry measurements were conducted of a wing-tip vort...
Planar and stereo particle image velocimetry measurements were conducted of a wing-tip vortex decayi...
A wide range of unsteady phenomena relevant to vortex flows over stationary and maneuvering delta wi...
Simplified models of the vortex distribution over cylindrical surfaces are developed. The effect of ...
Separation-induced leading-edge vortices can dominate the flow about slender wings at moderate to hi...
Experimental x-wire measurements of the flowfield above a 70 and 75 deg flat plate delta wing were p...
The vortex dynamics of leading-edge vortices on plunging high-Aspect-ratio (ARÂ =Â 10) wings and air...
An assessment of the influence of airfoil geometry on delta wing leading edge vortex flow and vortex...
The velocity field near the apex region of moderately swept delta wings was measured in a water tunn...
A vortex filament-vortex core method for predicting aerodynamic characteristics of slender wings wit...
The qualitative responses of a trailing vortex core to change in its convective velocity produced by...
SEE A90-458458th AIAA Applied Aerodynamics Conference; Aug. 20-22, 1990; Portland, OR; United States...
The interaction of a vortex and a pipe flow, modelled as the Lamb–Oseen vortex and the Poiseuille fl...
An experimental investigation on vortex breakdown on delta wings at high angles of attack is present...
It is now known that Batchelor's trailing-line vortex is extremely unstable to small amplitude distu...
Time-resolved stereoscopic particle image velocimetry measurements were conducted of a wing-tip vort...
Planar and stereo particle image velocimetry measurements were conducted of a wing-tip vortex decayi...
A wide range of unsteady phenomena relevant to vortex flows over stationary and maneuvering delta wi...
Simplified models of the vortex distribution over cylindrical surfaces are developed. The effect of ...
Separation-induced leading-edge vortices can dominate the flow about slender wings at moderate to hi...
Experimental x-wire measurements of the flowfield above a 70 and 75 deg flat plate delta wing were p...
The vortex dynamics of leading-edge vortices on plunging high-Aspect-ratio (ARÂ =Â 10) wings and air...
An assessment of the influence of airfoil geometry on delta wing leading edge vortex flow and vortex...
The velocity field near the apex region of moderately swept delta wings was measured in a water tunn...
A vortex filament-vortex core method for predicting aerodynamic characteristics of slender wings wit...
The qualitative responses of a trailing vortex core to change in its convective velocity produced by...
SEE A90-458458th AIAA Applied Aerodynamics Conference; Aug. 20-22, 1990; Portland, OR; United States...
The interaction of a vortex and a pipe flow, modelled as the Lamb–Oseen vortex and the Poiseuille fl...
An experimental investigation on vortex breakdown on delta wings at high angles of attack is present...
It is now known that Batchelor's trailing-line vortex is extremely unstable to small amplitude distu...
Time-resolved stereoscopic particle image velocimetry measurements were conducted of a wing-tip vort...
Planar and stereo particle image velocimetry measurements were conducted of a wing-tip vortex decayi...
A wide range of unsteady phenomena relevant to vortex flows over stationary and maneuvering delta wi...