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Simulation results demonstrate that the boundary layer edge of complex hypersonic 3D flow can be obtained accurately with the help of grid pretreating method.
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Also, they clearly indicate the singular behavior of interlaminar normal and shear stresses in the boundary-layer regions near the edges of the shells.
In summary, we have found that there is a boundary layer near the edges of the strip.
In particular, it is shown that the flow is dominated by the motion of vortices which result from the shedding of boundary layers from the edges of the stack.
The domain is 0 ≤ η ≤ η ∞, where η ∞ is the edge of the boundary layer of the basic flow.
Consider the boundary layer term of Γ.
It is observed that increasing the number of layer subdivisions, p, has no significant effect on the numerical value of interlaminar stress σ z within the boundary layer region of the laminate, especially at the free edge (i.e., y = b) because of the interface-edge junction of similar layers (i.e., 90°/90°).
The first is the creation of a boundary layer near the edges y=±w/2 due to the boundary condition (11) there.
Simplifications of each of these equations are made in the context of boundary-layer processes.
According to the triaxiality analyses, the sharp curves of void boundaries along with the edges of solder layer are the most susceptible sites for crack initiation.
The existence of a separated boundary layer near the trailing edge of the airfoil at an angle of attack of 4.2 degree has been experimentally identified by a surface mounted hot-film arrays technique.
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Justyna Jupowicz-Kozak
CEO of Professional Science Editing for Scientists @ prosciediting.com