An inviscid-viscous interaction approach to the calculation of dynamic stall initiation on airfoils
MetadataShow full item record
An interactive boundary-layer method is described for computing unsteady incompressible flow over airfoils, including the initiation of dynamic stall. The inviscid unsteady panel method developed by Platzer and Teng is extended to include viscous effects. The solutions of the boundary-layer equations are obtained with an inverse finite-difference method employing an interaction law based on the Hilbert integral, and the algebraic eddy-viscosity formulation of Cebeci and Smith. The method is applied to airfoils subject to periodic and ramp-type motions and its abilities are examined for a range of angles of attack, reduced frequency, and pitch rate.
The article of record as published may be found at https://doi.org/The article of record as published may be found at http://dx.doi.org/10.1115/1.2929307
Showing items related by title, author, creator and subject.
Lee, Hee Woo (1986-03);This thesis treats the problem of incompressible two-dimensional steady flow past airfoils or airfoil combinations at large angles of attack. A panel method was developed to compute the inviscid flow over two cylinders, ...
Platzer, Maximilian F. (The United States of America as represented by the Secretary of the Navy, Washington, DC (US), 1999-11-02);A new method for boundary layer energization and boundary layer propulsion for use on vehicles moving through fluids, which comprises mounting small airfoils parallel or perpendicular to the vehicle's surface, said airfoils ...
Alexandris, Georgios (Monterey, California. Naval Postgraduate School, 1998-06);Supersonic flow past two oscillating airfoils is analyzed using an elementary analytical theory valid for low frequencies of oscillation. The airfoils may have arbitrary stagger angle. This approach generalizes Sauer' ...