Numerical Investigation of the Circumferential Angle of the Axisymmetric Bypass Dual Throat Nozzle

One of the modern concept of Fluidic Thrust Vectoring (FTV) is the Bypass Dual Throat Nozzle (BDTN). In the present work this nozzle with a circular cross-section which is called ABDTN has been studied numerically. In this method a bypass channel separates the main nozzle flow into two parts as a primary and secondary flow from upstream of the nozzle throat. The results of the interaction between the main nozzle flow and the bypass channel flow are investigated as a secondary injection. The present work discusses about the performance parameters of the ABDTN, including thrust deflection angle, resultant thrust ratio, discharge coefficient, and thrust vectoring efficiency over a range of nozzle pressure ratios (NPR) to obtain the effects of different circumferential angles (α) of the bypass channel. The results of increasing α show that the maximum deflection angle will decrease from 24º to 21º at the nozzle pressure ratio of 1.5.