Optimization of Bypass Flow Introduction Angle in Dual-Throat Nozzle

Abstract

This research paper investigates the optimal angle for introducing a bypass jet in rocket engines for thrust vectoring. Numerical simulations using a finite-volume method were performed to test a range of bypass jet angles and their effect on flow performance. Results indicate that the optimal bypass jet angle is between 40 and 50 degrees, with larger angles leading to decreased thrust. These findings demonstrate the potential for bypass jet introduction to improving thrust vectoring in rocket engines, especially in the supersonic regime. Such insights may inform the development of more efficient and effective rocket engines for various applications, including satellite launches, space exploration, and defense. Overall, this study represents a valuable contribution to the field of rocket propulsion and may drive advances in engine design and performance.