Prosser, D., Crassidis, A. and Ghosh, A. (2011) The Applicability of Unsteady Vortex Panel Methods to the Design of Hovering Flapping-Wing Micro Air Vehicles. AIAA Atmospheric Flight Mechanics Conference, Portland, 8-11 August 2011, 1-19.
http://enu.kz/repository/2011/AIAA-2011-6392.pdf

has been cited by the following article:

• TITLE: Non-Dimensional Values for Convergence of Lift Prediction Using Panel Method

  AUTHORS: Rodas I. Fernando, Castillo C. Pablo

  KEYWORDS: Aerodynamics, Panel Method, Convergence, Lift, Inviscid, Non-Frozen Wake

  JOURNAL NAME: Open Journal of Fluid Dynamics, Vol.7 No.1, January 18, 2017

  ABSTRACT: This paper presents an implementation and posterior analysis of the convergence of the panel method. The implemented panel method is based on vortex lines and an unsteady wake on a flat plate as a wing. The main goal of the study was to discover parameters and their values range to obtain convergence of the solution. Results of lift convergence in function of control panel’s position, the effect of the size of the wake panels, the dimension of the wake, and the computation time are quantitatively described. The lift results are similar to the predictions by the lifting-line theory and the wake exhibited an expected shape, showing wingtip, and start vortices. Geometric parameters and non-dimensional values were developed to increase accuracy and stability of the method.