Inverse shape design method based on pressure and shear stress for separated flow via Elastic Surface Algorithm

Noorsalehi, Mohammad Hossein; Nili-Ahmadabadi, Mahdi; Kim, Kyung Chun

doi:10.1080/17415977.2021.1914604

Cited by 1 publication

(1 citation statement)

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“…They applied the shear stress distribution as the target function to reduce the size and length of the separation zone. Noorsalehi et al [66] developed the ESA for the inverse design in external separated flows by considering a linear combination of normalized pressure and shear stress distribution as the target flow parameter. They upgraded the ESA for separated flows by removing the geometrical filtrations and defining dynamic spines instead of the vertical spines.…”

Section: Introductionmentioning

confidence: 99%

Aerodynamic Inverse Design of Transonic Compressor Cascades with Stabilizing Elastic Surface Algorithm

et al. 2021

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The upgraded elastic surface algorithm (UESA) is a physical inverse design method that was recently developed for a compressor cascade with double-circular-arc blades. In this method, the blade walls are modeled as elastic Timoshenko beams that smoothly deform because of the difference between the target and current pressure distributions. Nevertheless, the UESA is completely unstable for a compressor cascade with an intense normal shock, which causes a divergence due to the high pressure difference near the shock and the displacement of shock during the geometry corrections. In this study, the UESA was stabilized for the inverse design of a compressor cascade with normal shock, with no geometrical filtration. In the new version of this method, a distribution for the elastic modulus along the Timoshenko beam was chosen to increase its stiffness near the normal shock and to control the high deformations and oscillations in this region. Furthermore, to prevent surface oscillations, nodes need to be constrained to move perpendicularly to the chord line. With these modifications, the instability and oscillation were removed through the shape modification process. Two design cases were examined to evaluate the method for a transonic cascade with normal shock. The method was also capable of finding a physical pressure distribution that was nearest to the target one.

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Section: Introductionmentioning

confidence: 99%