Numerical Investigation on the Thrust Vectoring Performance of Bypass Dual Throat Nozzle

Modern aircraft and missiles are gradually integrating thrust vector control systems to enhance their military capabilities. Bypass Dual-Throat Nozzle (BDTN) is a new fluidic vectoring technique capable of achieving superior performance with large angles low loss. In this study, we analyzed the flow characteristics parameters BDTN by varying bypass angle, nozzle convergence width. The governing equations solved according finite volume discretization compressible RANS coupled Renormalization Group (RNG) k-ϵ turbulence model for Pressure Ratio (NPR = 2~10) capture significance under-expanded over-expanded jets. Results show that decreasing angle from 90° 35°, there 6% increase in while efficiency enhanced 18%. However, decrease 3% discharge coefficients also observed. When was increased 22° 37°, coefficient, coefficient 2%, 1%, 0.26%, respectively. Moreover, 8% reducing 37° 22°. Based on investigated parameters, it determined does not significantly influence performance, however, width have significant effect performance.