Determination of the critical attack angle at which dynamic stall occurs
has been a focus of research over the last few decades. This angle is
usually determined by solving the Navier-Stokes equations, which
includes viscosity, pressure, gravity, and acceleration terms. However,
this article predicts the critical attack angle using Euler equations
that do not contain viscous terms. The key contribution is the use of
the Euler equations to capture the vortices and predict stall dynamics.
The Euler equations are integrated and the resulting equations are
discretized by the finite volume method. A first-order upwind-based
method is used to calculate the convective fluxes at the cell boundaries
in the finite volume approach. A NACA 0012 airfoil is chosen for this
study at various attack angles with a Mach number of 0.3. Based on the
justification of Crocco's theorem, the Euler equations successfully act
as Navier-Stokes equations. The vortex patterns are found to behave
independently of the artificial dissipation. All the vortices are
successfully predicted using the inviscid governing equations. The
obtained numerical results are validated by the existing experimental
and numerical data.