Experimental Investigation of Active Control of Thrust Vectoring Nozzle Flow Fields.

摘要

Fluidic thrust vector control is examined in a supersonic rectangular jet having a 4:1 aspect ratio. Experiments conducted at a Mach number of 2 reveal that the thrust vector angle of the jet can be continuously varied by up to at least 16 deg by applying a counterflowing stream to one of the primary jet shear layers. A technique using counterflow eliminates the bistable response known to plague fluidic elements and is shown to be effective in both hot and cold supersonic jets. Results are presented for jet stagnation temperatures between 300 deg K and 670 deg K. Measurements indicate that the thrust vector control is both efficient as well as a linear function of the static pressure developed in the counterflowing stream. The typical power required to vector the jet at 16 degrees was estimated to be less than 1% of the power developed in the primary jet. Thrust vector control employing counterflow has several advantages over current technologies, the most important of which is the elimination of movable control surfaces which add considerable weight to the aircraft. Thrust vectoring nozzle, Active control.