This paper provides an simulation analysis of stage separation of hypersonic vehicle,three-degrees-of-freedom dynamics equation of hypersonic vechicle designed;hypersonic vechilcle longitudinal separation dynamics and non-axisymmetrical separation flow field analysed;the boundary of tail-flow fixed;the characters of aerodynamic coefficient discussed;the force confirmed.

Research of asymmetric vortex characteristic about forebody of slender wing and body;

When a fighter aircraft or missile flies at high angle of attack(AOA),asymmetric vortexes are produced from the forebody and induce strong side force and yawing moment.

In order to study the Reynolds number effects with zonal behaviors on the asymmetric vortex flow over slen- der body,the experimental investigations were carried out in D-4 Low Speed wind tunnel of BUAA and the NF-3 wind tun- nel of Northwest Polytechnic University(NPU)on a 3D pointed tangent ogive/cylinder model with f meness ratio 6 in Reynolds numbers range 0.

Experimental study of Reynolds numbers effect on asymmetric vortices and their aerodynamic characteristics over a slender body;