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Comparison of the transitional boundary layer during pitching and heaving motions

Akhlaghi, H ; Sharif University of Technology | 2021

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  1. Type of Document: Article
  2. DOI: 10.2514/1.C035858
  3. Publisher: AIAA International , 2021
  4. Abstract:
  5. In an experimental study, investigation is performed based on the surface-mounted hot-film sensors and surface pressure and rake pressure measurements. The boundary-layer (BL) events such as laminar separation (LS), transition onsets, and variations of the wall shear stress are discussed and compared for both pitching and plunging oscillations for various cases of before, within, and beyond the static stall angle of attack (AOA) conditions. All experiments are conducted in a low-speed wind tunnel. The surface pressures are measured using differential pressure sensors with a range from 0.075 to 1.0 psi and with a maximum error of 0.15% of their full span. In addition, the wake profile behind the model is studied using two different rakes located at a distance of 1.5c behind the airfoil
  6. Keywords:
  7. Angle of attack ; Shear stress ; Wind tunnels ; Differential pressure sensor ; Heaving motion ; Laminar separations ; Low-speed wind tunnel ; Surface pressures ; Surface-mounted hot films ; Transitional boundary layers ; Wall shear stress ; Laminar boundary layer
  8. Source: Journal of Aircraft ; Volume 58, Issue 1 , 2021 , Pages 203-209 ; 00218669 (ISSN)
  9. URL: https://arc.aiaa.org/doi/10.2514/1.C035858