Version 1
: Received: 17 February 2024 / Approved: 19 February 2024 / Online: 20 February 2024 (04:34:07 CET)
How to cite:
Sereez, M.; Abramov, N.; Goman, M. CFD Simulations and Phenomenological Modelling of Aerodynamic Stall Hysteresis of NACA 0018 Wing. Preprints2024, 2024021051. https://doi.org/10.20944/preprints202402.1051.v1
Sereez, M.; Abramov, N.; Goman, M. CFD Simulations and Phenomenological Modelling of Aerodynamic Stall Hysteresis of NACA 0018 Wing. Preprints 2024, 2024021051. https://doi.org/10.20944/preprints202402.1051.v1
Sereez, M.; Abramov, N.; Goman, M. CFD Simulations and Phenomenological Modelling of Aerodynamic Stall Hysteresis of NACA 0018 Wing. Preprints2024, 2024021051. https://doi.org/10.20944/preprints202402.1051.v1
APA Style
Sereez, M., Abramov, N., & Goman, M. (2024). CFD Simulations and Phenomenological Modelling of Aerodynamic Stall Hysteresis of NACA 0018 Wing. Preprints. https://doi.org/10.20944/preprints202402.1051.v1
Chicago/Turabian Style
Sereez, M., Nikolay Abramov and Mikhail Goman. 2024 "CFD Simulations and Phenomenological Modelling of Aerodynamic Stall Hysteresis of NACA 0018 Wing" Preprints. https://doi.org/10.20944/preprints202402.1051.v1
Abstract
Computational simulations of three-dimensional flow around a NACA 0018 wing with an aspect ratio of AR=5 are carried out using the Unsteady Reynolds-Averaged Navier-Stokes (URANS) equations with the Shear-Stress Transport turbulence model closure. Simulations were performed to capture the aerodynamic stall hysteresis using a developed Pseudo-Transient Continuation (PTC) method based on a dual time step approach in the CFD code OpenFOAM. The flow was characterized by an incompressible Mach number of M=0.12 and a moderate Reynolds number Re=0.67×10^6. The results obtained indicate the presence of a noticeable aerodynamic hysteresis in the static dependencies of the force and moment coefficients, as well as the manifestation of bi-stable flow separation patterns, accompanied by the development of asymmetry in the stall zone. The URANS simulation results are in good agreement with the experimental data obtained for the NACA 0018 finite aspect ratio wing from the low-speed wind tunnel under the same test conditions. A new phenomenological bifurcation model of aerodynamic stall hysteresis under static and dynamic conditions is formulated, which is proven to be able to closely match the experimental data.
Keywords
Static Hysteresis; Dynamic Stall; Dual Time Stepping; OpenFOAM; Phenomenological Bifurcation Model
Subject
Engineering, Aerospace Engineering
Copyright:
This is an open access article distributed under the Creative Commons Attribution License which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.
