Unsteady Aerodynamic Characteristics of Airfoil with Moving Spoilers

摘要

A discrete vortex model is developed for simulating unsteady separated flow around an airfoil with a conventional or base-vented spoiler when the spoiler is deployed at a finite speed. The airfoil and spoiler are discretized by linear segments. A linear distribution of vortices and a constant source are used to represent each segment, forming the basis of the present method. Discrete vortices are shed from each separation point. A new sharp-edge condition is formulated such that the location and strength of the nascent vortex near a separation point are determined by means of the continuity equation and the momentum principle.