Compared with symmetrical extraction algorithm and polygonal approximation algorithm, the algorithm can extract contour's typical character of the blade effectively, for example, leading edge and trailing edge.

The smart rotor with active trailing edge is a new system for reducing the vibration which can adjust the air load of the blade to actively counteract the main harmonic of the force to the fuselage by controlling the deflection of the trailing edge.

In this paper, we mainly investigate trailing edge noise of the clean wing which is one of the most important airframe noise sources on an aircraft flying.

Their availability, stability, and robustness are proved by simulation on both model rotor and real rotor with the effect of the design parameters of the flap studied.

Two step Roe scheme developed by Rogers was used to solve the artificial compressible INS equations,in order to simulate the laminar separation of the E387 airfoil near the tailing-edge at low Reynolds number(Re=6.0×10~4,1.0×10~5,2.0×10~6) and different angle-of-attack(α=0°,4°,7°),corresponding to the long laminar separation bubble.

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.

An investigation Was conducted to determine the effects of geometrical variables on longitudinal and lateral aerodynamic characteristics of parawings at low speed. The variables under study included variations in the shape of the trailing-edge,. the rib-strips, the apex angles, the strakes, the chord of the outer part of the wing, the shape of the keel, the slackness ratio, and the dihedral ange.The results of the study indicate that, for single keel two lobed parawing, the shape of the trailing-edge has a significant...

An investigation Was conducted to determine the effects of geometrical variables on longitudinal and lateral aerodynamic characteristics of parawings at low speed. The variables under study included variations in the shape of the trailing-edge,. the rib-strips, the apex angles, the strakes, the chord of the outer part of the wing, the shape of the keel, the slackness ratio, and the dihedral ange.The results of the study indicate that, for single keel two lobed parawing, the shape of the trailing-edge has a significant effect on the aerodynamic characteristics, the maximum lift-drag ratio with inward curved trailing edges can be much higher than that with straight trailing edges. Adding ribs to the flexible wing surface results in a decrease in drag and increase in lift-drag ratio . For parawings of higher apex angles , incresing the apex angle results in higher lift-drag ratio, and adding a small strake can increase the maximum lift coefficient and improve the stall characteristics. The lift characteristics can also be improved using a curved keel with proper curvature .Increasing slackness ratio exhibits a stabilizing increment in the directional stability Incresing the dihedral angle exhibits a stabilizing increment in the lateral stability, but contributes a destabilizing effect to the directional stability. within a certain range, the variation of the dihedral angle plays an inverse role on the lateral as well as the directional stability as that of the slackness ratio .

Many of the current fighter aircraft use maneuvering flaps to enhance air combat maneuverability. Based on wind tunnel tests, this paper deals with the ability and causes of maneuvering flaps to decrease drags, the effects of the flap span, the flap chord, the strake and the wing plane form on the aerodynamic characteristics of the maneuvering flap, the matching of leading-edge and tailing-edge flaps, the improvement in the large angle-of-attack flying quality. This study shows that maneuvering flap is an effective...

Many of the current fighter aircraft use maneuvering flaps to enhance air combat maneuverability. Based on wind tunnel tests, this paper deals with the ability and causes of maneuvering flaps to decrease drags, the effects of the flap span, the flap chord, the strake and the wing plane form on the aerodynamic characteristics of the maneuvering flap, the matching of leading-edge and tailing-edge flaps, the improvement in the large angle-of-attack flying quality. This study shows that maneuvering flap is an effective measure to improve air combat capability of fighter aircraft at large angles of attack. Maneuvering flaps can effectively control the flow Separation and decrease the drag at large angles of attack. They also can expand the buffet boundary and decrease the buffet intensity. As a result, the large angle-of-attack flying quality can be significantly improved by utilization of maneuvering flaps. To the end of optimum comprehensive effect, the effects on both the aircraft structure and the system must be taken into account during the choice of the parameters of maneuvering flaps.

The three dimensional Navier-Stokes equation describing the recirculating flow field behind the trailing edge of the Barchan Dune vortex generator was solved numerically by the Artificial Damping and Compressibility Method. The structure and stability of the ox-horn shaped vortex scroll were analysed. Due to the arching effect and the pumping effect of the diverging sources at the tips, the Barchan Dune vortex serolls possess tenacious anti-disturbance property. Experimental results revealed that, compared with...

The three dimensional Navier-Stokes equation describing the recirculating flow field behind the trailing edge of the Barchan Dune vortex generator was solved numerically by the Artificial Damping and Compressibility Method. The structure and stability of the ox-horn shaped vortex scroll were analysed. Due to the arching effect and the pumping effect of the diverging sources at the tips, the Barchan Dune vortex serolls possess tenacious anti-disturbance property. Experimental results revealed that, compared with V-gutter at the same blockage ratio, the dragloss of the Barchan Dune vortex generator was reduced by 75-80%; the range of lean blow-out limits was extended to about 8 folds at the same inflow rate; and the ignition of combustible mixture was much easier. The experiments supported the diagnostic criterion for vortex stability proposed by Gao Ge in reference [1].