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Based on this concept, a single-stage, low-reaction and low-speed axial compressor is constructed in association with analysis and computation of boundary layer suction on vanes with the aid of a three-dimensional numerical approach.
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OGVs are hollow blades with two slots designed on the suction side which can better control the flow on the suction surface through boundary layer suction.
Experimental results indicate that boundary layer suction can improve the compressor characteristics and the best suction methodology varies along the operating line.
The characteristic features of the concept are made clear through its comparison with the MIT boundary layer suction compressor.
The accuracy of Menter and Langtry's transition model applied for simulating the flow with boundary layer suction is validated.
The results attest to the effectiveness of this way to control separation in blade cascades by the boundary layer suction and the feasibility of this proposed design concept.
There is introduced a new low-reaction, highly-loaded axial compressor design concept which is coupled with boundary layer suction method.
Around the peak efficiency point, boundary layer suction from the slots of OGVs is the best choice in improving the efficiency, but it causes a 0.1% loss in the total pressure ratio.
The control of boundary layer separation on the suction side of an airfoil at high angle of attack has been renewed by the possibilities of active control.
The problem of unsteady flow and heat transfer in the laminar boundary layer on a linearly accelerating surface with suction or blowing in the absence and presence of a heat source or sink is considered.
With further increase in attack angle, the flow over the suction surface separates near the leading edge of the airfoil and the boundary layer on the pressure surface keeps fully attached flows on the airfoil surface, resulting in the disappearance of tonal noise.
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