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Thrust optimization of synthetic jets for maximal thrust generation is achieved by enforcing the jet formation number to be around 4. Prototypes of such actuators are built and tested for underwater maneuvering and propulsion.
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Image analysis suggests that lift-based thrust should dominate during the early part of the downstroke, and drag-based thrust should dominate during the late part of the downstroke when thrust generation is maximal (Wyneken 1997; Becking et al., 2004).
The maximal velocity of the proposed motor is 735 mm/s and the maximal thrust is 1.1 N.
The no-load speed and maximal thrust force of the prototype motor at three operation modes are tested.
For flight speeds above Mach 2.5 or 3, the ram-pressure ratio becomes so high that a turbocompressor is no longer necessary for efficient thrust generation.
As has been seen, ram pressure plays an increasingly important role in the thermodynamic cycle of power and thrust generation of the jet engine at supersonic flight speeds.
The effects of several flapping modes on the lift and induced drag (or thrust) generation are also investigated.
The dynamic roles of specific surface features in thrust generation, drag reduction and anchoring on the free surface are considered.
The method is validated by an extensive numerical study of the thrust generation of an oscillating airfoil, involving comparisons with reliable experimental results.
Experimental results show that the suggested motor has structural stability and high dynamic performance, such as no-load speed of 1.4 m/s and maximal thrust of 43 N, meeting the requirements for absolute gravimeters.
Therefore, a natural continuation process consists in starting with larger values of the maximal thrust and then decreasing step by step the maximal thrust.
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