COMPUTATIONAL INVESTIGATION OF DUAL THROAT FLUIDIC THRUST VECTORING NOZZLE
A computational study of dual throat fluidic thrust vectoring nozzle was conducted with solving the two-dimensional and three-dimensional Reynolds-averaged Navier-Stokes (RANS) equations. The 2-equation k- turbulence model, with second order closure, is used to model complex viscous flow features. Based on open literatures, three double throat fluidic thrust vectoring nozzle configurations were designed. The fluidic injection slot width was 0.28, 0.56 and 0.70 millimeter, respectively. The thrust ratio, thrust vectoring efficiency, thrust vectoring angle, and discharge coefficient were computed for the both nozzle concept, fluidic injection flow rate was from 0.50 to 2.76 percent of the primary flow rate. All simulations were computed at a static freestream Mach number of 0.05, a nozzle pressure ratio (NPR) of 4.0, and a fluidic injection angle of =150°.Computational results indicated that dual throat nozzle can achieve higher thrust-vectoring efficiency than other fluidic techniques documented in open literature. With the same fluidic injection flow rate, the length of penetration of the secondary injected flow and the blockage of the primary exhaust flow increased with the decreased fluidic injection slot width. The length of penetration of the secondary injected flow and the blockage of the primary exhaust flow increased with the increase of fluidic injection flow rate. The pressure in the cavity decreased with increased the blockage of the primary.exhaust flow. Therefore, the thrust vectoring angle increased,and the shock wave moved downstream.
Eriqitai Wang Qiang
School of Jet Propulsion, Beijing University of Aeronautics & Astronautics, Beijing 100083
国际会议
昆明
英文
585-590
2006-09-18（万方平台首次上网日期，不代表论文的发表时间）