Flight Testing of a Blown Wing Configuration Aircraft

Abstract

The leading cause of fatalities and accidents in aviation comes from loss of control in general aviation. Loss of control can result from stalls or control surface or actuator failure. While conventional methods of addressing these problems historically relies on pilot training and multiple back-up systems performing the same function, there may be other methods of increasing safety. Research is ongoing for a blown wing concept by NASA, placing multiple propellers along the leading edge of the wing to augment lift generation by increasing the dynamic pressure may also provide additional benefits for control redundancy and stall prevention. A five-foot wing span RC model was modified to use six propellers mounted along the leading edge of the wings. Control characteristics of the aircraft was analyzed using blade element momentum theory along with examining linearized lateral direction dynamics. An attempt to empirically investigate the control characteristics through flight testing were partially successful. The aircraft successfully flew multiple times. However, approval for flying outdoors was not obtained, and the indoor space was not large enough for maneuvering and testing. As a result, takeoffs followed by immediate landing were executed. Control characteristics were not investigated, because of the lack of space. Flaps were retrofitted to the aircraft in an attempt to reduce the airspeed, and the aircraft was flown again successfully.