Numerical simulation of unsteady flows past a delta wing using a 3-D vortex method;

Effects of free stream local disturbance on delta wing aerodynamics;

Numerical simulation to effects of trailing edge jet on delta wing vortices;

Unsteady structures over delta wings;

The effectiveness of the apex flaps to control the vortex breakdown on a 70° sweep angle delta wings was studied experimentally.

The progress in numerical simulations of separation and vortical flows on delta wings (including double-delta wings, strake-delta wings and close-coupled canards) was summarized in this paper.

The effects of Gurney flap on double delta wing aerodynamic performance in low speed wind-tunnel tests;

Experimental investigation of the vortex characteristic over 75°/45°double delta wing;

Compared with a delta wing aircraft, the double delta wing configuration has better aerodynamic performance at high angles of attack.

Experimental study on pressure measurement distribution of double-delta wings;

The vortex visualization and surface pressure distribution for a 75°/45°double-delta wing were carried out in the water tunnel and in the low speed wind tunnel of BUAA.

The vortex visualization and surface pressure distribution measurement for a 75°/60° double-delta wing were carried out in the water tunnel and in the low speed wind tunnel of BUAA.

A sharp-edged flat-plate delta wing of 82.

A force measurement experimental study was performed on a flat-plate delta wing of 82.

For the flat-plate delta wing at zero sideslip, the theory is that the vortices over the wing are conical, symmetric, and stable for all angles of attack, but adding a low dorsal fin to the wing would destabilize the vortices and the vortex pair is unstable and become non-conical, or non-stationary, or asymmetric, or all of them.