Counterflow thrust vectoring of supersonic jets

Abstract

Fluidic thrust vector control is examined in a supersonic rectangular jet having a 4:1 aspect ratio and for jet stagnation temperatures between 300 and 670 K. Experiments conducted in a nominally ideally expanded Mach 2 jet reveal that thrust can be continuously vectored up to at least 16 deg by creating a secondary counterflowing stream between the primary jet and an adjacent curved surface. Thrust vector control using counterflow is shown to be effective in both cold and moderately heated supersonic jets and to perform free of bistable or hysteretic effects. Measurements indicate that proportional thrust vector control can be achieved with less than 4% thrust loss and requiring secondary mass flow rates less than approximately 2% of the primary jet.