Experimental Study on the Performance Characteristics of Thrust Vectoring Nozzle of Transonic Aircraft

In this study, the performance characteristics of a scaled thrust vectoring nozzle applicable to transonic aircraft were analyzed using a supersonic wind tunnel test facility.The investigation was conducted through jet flow Schlieren visualization and thrust measurements at various nozzle deflection angles.The test nozzle was a 0.264 scale model based on the length of a virtual aircraft engine.The nozzle exit had a rectangular shape with an aspect ratio of 5, and thrust vectoring was achieved by a secondary flap at deflection angles of 0, 5, 10, and 15.Experimental results confirmed that the designed scaled thrust vectoring nozzle achieved effective thrust vectoring under an NPR of 2.0 operating conditions. . 0.264 . 5 , 0, 5, 10, 15 4 .