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The aeroelastic responses of the blade were obtained by coupling these aerodynamic and structural models.
The control data points of an impeller or a blade were obtained by using the reverse engineering method.
Preform designs for the forging process of an airfoil section blade were obtained by using backward simulation approach and the influence of dynamic boundary conditions on preform design for deformation uniformity was investigated.
From a 4 cm2 area, bacterial swabs (via Epicentre swabs) and scrapes (via sterile disposable surgical blade) were obtained and incubated in enzymatic lysis buffer and lysozyme for 30 minutes at 37°C.
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The design data for a turbine blade is obtained using Reverse Engineering technique.
The forward-skewed blade was obtained by the optimization design of the radial blade and CFD technique.
The time domain aeroelastic responses of the United States NREL National Renewable Energy Laboratoryy) offshore 5-MW wind turbine blade are obtained.
Secondly, displacement responses of cracked blade are obtained, and the results with CHE and contact element are identical.
The nonlinear periodic transient responses and vibration hub loads of the composite blade are obtained by solving coupled equations using the Newton Raphson numerical procedure.
The equations of motion and the boundary conditions for the coupled flexural and torsional vibration of the blade are obtained by using Hamilton's principle.
The stiffness of the cracked blade is obtained with CHE and proved to be time-varying and dependent on the alternating loads.
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