For trailing edge problem,the integral equation of Kutta condition and the differential equation of vorticity conservation are solved simultaneously,and the vorticity distribution Υ(y)is found with t (time) and x (longitudinal location) as parameters.

Water-tunnel experiment re- sults indicate that the reason for drag reducing of swept wing-tip is that when the angle of attack is not Zero,the strength tip vortex of the wing is weakened by the combined effect of the leading edge and trailing edge vortices of the swept wing-tip.

Incompressible Reynolds averaged Navier Stokes equations are solved using pseudo compressibility method for the simulation of incompressible flow over a delta wing with trailing edge jet at high angles of attack. The Beam Warming implicit approximate factorization scheme and MML algebraic turbulence model are utilized in the simulation.

In addition, the trailing edge jets may weaken or even eliminate the mixing phenomenon of the leading edge vortex, which is in advantage of the flight control of aircraft.

It also indicate that in the wake integration method,the location of wake integration surface should be set in the distance of 0.6～1.0 relative chord length from the trailing edge.

Head shaking was attenuated by the subcutaneous infiltration of the local anesthetic procaine into the posterior border of the external auditory meatus.

The posterior border consists of a nebulous field of labeling and occasional barrel-like structures.

The setae on the posterior border of the telson were used for grooming the maxillipeds and the anterior mouthparts.

An anterior increased density, that parallels the posterior border of the sternum, was noted on the lateral radiograph of two children who were at first thought to have an accessory diaphragm.

Inflammatory changes along the posterior border of the pad may also be used to help differentiate effusion from acute synovitis on unenhanced MR examinations.

characterized by the absence of eyes and by the presence of the spermatheca and sharp depression at the posterior margin of the thoracic metasternite.

dorsoporum in having an external seminal vesicle much shorter than the cirrus sac, a longer cirrus sac extending posteriorly to the level of the posterior margin of the ventral sucker and a pretesticular ovary; from N.

chaetodoni in having a smaller body size, symmetrical testes, a longer cirrus sac extending posteriorly to the level of the posterior margin of the ventral sucker and a trilobed ovary; and from N.

simentiensis differ in size and shape from those on the posterior margin of the haptor.

The structural correlate for DPL is a small clear patch of skin lying at the posterior margin of each opercular cavity.

On the anterior edge of pereionite 1 and the posterior edge of pereionite 5, specialized areas were found that allow penetration of the male's dactyli in the inter-segmental spaces of the female.

Using six cadaver knees, an isometric point was found 3?mm distal to the posterior edge of Blumensaat's line, at the 10:30-11:00 o'clock position in right knees, at the antero-proximal edge of the anatomic ACL attachment.

During both the upward and downward movements of the wing, its posterior edge lagged behind the anterior one, i.e.

Before penetrating the mussels, the worm first straddles the valves at the posterior edge of the shell and then, after having digested the posterior adductor muscle, removes and swallows the soft parts of the prey.

Smaller C4 and C5 tubules, located at the posterior edge, contained only relict oocytes.

The magnitude of this flow circulation is determined from the condition under which the flow leaves the trailing edge of the body (the analog of the Chaplygin-Zhukovskii postulate in potential flow).

We solve the problem of the natural oscillations of a gas flowing past a cascade of flat plates under the Joukowsky-Chaplygin condition that the velocity at the trailing edge of the profiles is finite.

The formation of a laminar wake in the flow behind a shock wave when the latter is shed from the trailing edge of a semi-infinite plate is investigated in this paper.

An analytic solution of the problem of the wake in the neighborhood of the trailing edge is obtained, from which it follows that, in contrast to [2], there is no line of singularities in the nonstationary boundary-layer equations in the flow domain.

This fact is also verified by the analysis of the flow in the neighborhood of a line of tagged particles leaving the trailing edge simultaneously with the shock wave.

Lagrangian coordinates were introduced to investigate the unsteady boundary layer separation of elliptic cylinder at angle of attack. The; forward-movement of the separation point with time was calculated. As well as the first occurence of separation. It was. also found that the separation pattern would change, as expected, from rear-separation to fore-separation as the angle of attack increased.In respect to the numerical methodogy, coordinate transformations were introduced to map the nonuniform mesh points...

Lagrangian coordinates were introduced to investigate the unsteady boundary layer separation of elliptic cylinder at angle of attack. The; forward-movement of the separation point with time was calculated. As well as the first occurence of separation. It was. also found that the separation pattern would change, as expected, from rear-separation to fore-separation as the angle of attack increased.In respect to the numerical methodogy, coordinate transformations were introduced to map the nonuniform mesh points in the physical plane to the uniform mesh points in the auxialliary plane to simplify the finite difference formula, and the complicated moving-boundary problem was treated in a fixed-boundary manner.

Hummel's experiment on the rolling-up and interaction of the leading-edge and trailing-edge vortex sheets at slender delta wing is modeled numerically by a simple two-dimensional theory. The numerical results show that the trailing-edge vortex sheet will roll-up at the downstream of the wing, in the presence of the leading-edge vortex, and the direction of the circulation of the leading-edge vortex is oppsite to the trialing-edge vortex. The numerical results are in good agreement with the experiment. This work...

Hummel's experiment on the rolling-up and interaction of the leading-edge and trailing-edge vortex sheets at slender delta wing is modeled numerically by a simple two-dimensional theory. The numerical results show that the trailing-edge vortex sheet will roll-up at the downstream of the wing, in the presence of the leading-edge vortex, and the direction of the circulation of the leading-edge vortex is oppsite to the trialing-edge vortex. The numerical results are in good agreement with the experiment. This work is important to further understand o'f the downstream flow-field of a wing.

The present paper deals with the slender body theory of flexible undulating lifting surface.The flows about leading edge problem,trailing edge problem and the second leading edge problem(i.e.the Ieading edge problem with oncoming vortices from upstream) are investigated respectively and as a result a unified solution is obtained.For trailing edge problem,the integral equation of Kutta condition and the differential equation of vorticity conservation are solved simultaneously,and the vorticity distribution Υ(y)is...

The present paper deals with the slender body theory of flexible undulating lifting surface.The flows about leading edge problem,trailing edge problem and the second leading edge problem(i.e.the Ieading edge problem with oncoming vortices from upstream) are investigated respectively and as a result a unified solution is obtained.For trailing edge problem,the integral equation of Kutta condition and the differential equation of vorticity conservation are solved simultaneously,and the vorticity distribution Υ(y)is found with t (time) and x (longitudinal location) as parameters.In the study of the second leading edge problem,the displacement effect of vortex sheet from the plane of symmetry is taken into account and thereby the difficulty of overlapping vortex sheet and the lifting surface is overcome.It can be shown that when the overlapping vortex sheet approaches close to the body surface infinitely,its effect on the flow vanishes.It is found that the hydrodynamic effect of a vortex sheet can be represented b y a single parameter denoted as W,which has the dimension of velocity and is a weighted average of vorticity induced velocity on the body surface.