Abstract
The characteristics of a subsonic nozzle with Fluidic Thrust Vectoring (FTV) in the pitch angle are investigated experimentally using a wind tunnel. The transient response of the FTV nozzle is also tested by mounting it on an aircraft flying at 25m/s. The FTV nozzle is designed so that a secondary jet branched from the main flow is joined at the nozzle throat and the main flow is separated from the nozzle wall surface. The deflection angle and deceleration rate of the main flow are measured with a pitot tube, and flow is visualized using a laser light sheet. The deflection angle without ventilation to the wind tunnel is up to 14deg at 100% throttle. When the FTV nozzle is operated in an air stream of 11m/s in a wind tunnel, the deflection angle is suppressed to 40%. In addition, the flight test demonstrates that the system can be used to control the flight attitude in pitch angle. During flight, there are transient delays of 1.5 seconds in pitch angle and 3 seconds in flight altitude.
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