关键词: 火箭发射场坪, 排焰道口, 弯曲射流, 计算流体力学, 初始半宽, 速度比

Abstract: A method for analyzing the subsonic winding jet in the non-uniform wind field based on the theoretical formula of subsonic linear jet is proposed to research the change law of jet from the exhaust tunnel outlet on the launch site. The axis equation of the winding jet under the non-uniform wind field, and the approximate formulas of jet half-width, velocities on cross sections, flow mass and velocities on axis are derived, and the velocities of incompressible winding jet under the conditions of constant wind speed, different initial half-widths and different speed ratios are calculated by using approximate formulas and computational fluid dynamics(CFD) method. The parameters of the approximate formulas are adjusted based on CFD results, and the influences of different initial half-widths and speed ratios on jet are analyzed. The results show that the approximate formulas can be used to calculate jet accurately, the change in initial half-width has little influence on jet, and the change in speed ratio has more influence on jet. The proposed method is feasible for analyzing the jet from exhanst tunnel outlet on rocket launch site.Key

Key words: rocketlaunchsite, exhausttunneloutlet, windingjet, computationalfluiddynamics, initialhalf-width, speedratio