trailing edge 
Solutions of the equations for the interaction zone in the neighborhood of the trailing edge of a thin profile at an angle of attack of the order O(Re1/16) in the separated flow regime are constructed numerically.


In all the regimes the value of the friction on the upper surface at the very end of the trailing edge remains a positive quantity.


The flow over the leading edge is assumed to be unseparated, and the separation at the trailing edge, if present, is assumed to be localized in the interior of the boundary layer.


In this case the satisfaction of the ChaplyginJoukowsky condition at the trailing edge ensures smooth flow over both the trailing and leading edges.


Calculation of base pressure and enthalpy behind a blunt trailing edge separating two supersonic streams with allowance for boun


A relatively simple method of calculating the parameters of the flow behind a blunt trailing edge separating two supersonic streams is developed.


Calculation of the base flow behind the rounded trailing edge of a twodimensional body separating two supersonic streams


The position of the center of pressure of starshaped bodies with an optimum trailing edge shape is investigated in relation to similarity parameters previously obtained theoretically.


A correspondence is established between the derivatives of the normal force with respect to the angle of attack for pyramidal starshaped bodies and bodies with the optimum trailing edge.


A comparison is made with the data for flow over a delta wing with given pressure at the trailing edge.


The calculated lift and cavitation number dependences remain bounded as the cavity end approaches the trailing edge of the hydrofoil.


Influence of the Trailing Edge of a Cavity on the Flow Fluctuation Intensity


The calculation results obtained for various cavity trailing edge contours are considered.


The strong effect of the geometry of the trailing edge on the flow parameter fluctuation intensity is demonstrated.


The flow pattern behind the cascade trailing edge is studied.


The problem of the design and aerodynamical calculation of a wing airfoil whose trailing edge glides over a plane horizontal surface is formulated and solved.


The linear problem of the timedependent inviscid flow past a thin symmetric airfoil with a control on its trailing edge deflected in accordance with an arbitrary law is considered.


Numerical solution of the problem of the mixing of the boundary layers shed from the trailing edge of a wing


During the mixing of viscous incompressible flows with different velocities, in the vicinity of a trailing edge an interaction region with a threelayer structure is formed, similar to that in the case of symmetric shedding with equal velocities.


The boundary layers developing on the upper and lower sides of the airfoil form a viscous mixing layer, or vortex sheet, which separates the flows downstream of the trailing edge.

