Vortex Controllers and Dynamic Analysis

The project objective are to develop a new software method for the dynamic analysis of aircraft and to prove the potential of unique high angle of attack Leading Edge Vortex Control (LEVC) devices. The software method will be an upgrade of a current computer code. The upgrade will include the effects of hysteresis during dynamic stall. New methods recently published employing state-space representation of aerodynamic characteristics will be used in the dynamic analyses. In Phase I the evaluation of the LEVC devices will be entirely by the computer code and flight simulation. The LEVC devices are expected to significantly improve control and delay aircraft departure to angles of attack well into post stall. Both static and dynamic analyses of the LEVC concept will be conducted. Computer codes will be run for two models. These are a General Aviation aircraft (C172), and a typical fighter aircraft (F16). Current stability parameters for these two will be updated. Data will be obtained to allow estimation of the effect of the LEVC concept on stability and control parameters for these two types of aircraft. Flight Simulation of the LEVC devices on these aircraft will conducted to evaluate the improvement. Wind tunnel and flight test will conducted for the concepts in Phase II.