The purpose of this paper is to develop an efficient method for analysing the gust response of an aerofoil using CFD. The new method was then applied to investigate how varying the characteristics of a sinusoidal gust affects flow separation over a NACA0012 aerofoil. A two-dimensional periodic gust was implemented in ANSYS Fluent using the User-Defined Function tool. A specialised mesh was designed to allow for accurate modelling of a gust past a NACA0012 aerofoil. The features a rounded trailing edge and an O-grid structure with 164,000 cells. An incompressible SIMPLE pressure-based solver was used in ANSYS Fluent. The k-ωSST turbulence with low Reynold’s corrections was chosen due to its effectiveness in modelling pressure-induced flow separation. The velocity-inlet boundary was defined by the user-defined function velocity components with an angle of attack, α.
|Publication status||Published - 28 May 2020|
|Event||33rd Scottish Fluid Mechanics Meeting - Heriot Watt University, Edinburgh, United Kingdom|
Duration: 28 May 2020 → 28 May 2020
|Conference||33rd Scottish Fluid Mechanics Meeting|
|Period||28/05/20 → 28/05/20|
- rapid-distortion theory
- leading-edge scattering
- sinusoidal gusts
- flow separation
Greenlee, G., Afsar, M., & Muhel, R. (2020). Investigating incipient separation for an aerofoil at an arbitrary orientation subjected to on oncoming gust. Paper presented at 33rd Scottish Fluid Mechanics Meeting , Edinburgh, United Kingdom.