摘要
针对某二元非对称喷管提出了两种可调方式(方案A和方案B),开展了不同落压比(NPR)的喷管风洞试验,获得了喷管壁面压力分布和流场纹影。根据风洞试验条件,进行了详细的三维数值模拟研究,并与试验结果进行对比,两者吻合良好,验证了本文所采用的数值模拟方法的可靠性。根据数值模拟与试验结果,得出了两种方案推力性能的差异。其中,方案B(喉道和出口面积均可调节)较方案A(仅喉道面积可调节)面积膨胀比更接近喷管理想膨胀比,因此方案B推力性能较好。在落压比为3.8时,方案B较方案A推力系数提高了8%。
Two adjustable programs （Plan A and Plan B） of a 2D adjustable asymmetric nozzle are presented in this paper. A tunnel test is carried out at different nozzle pressure ratios （NPR）, and the schlieren of the flowfield and the distribution of pressure along the nozzle wall are obtained. Based on the boundary conditions of the tunnel test, a detailed 3D numerical simulation is performed, and the results of the simulation are in good agreement with those of the tunnel test, which testifies the validity of the method of numerical simulation. A comparison of the results of 3D numerical simulation and tunnel test re- veals the difference of thrust performance between Plan A and Plan B. Plan B （in which the area of throat and outlet is ad- justable） is found to be better than Plan A （in which only the area of throat is adjustable） on thrust performance. When the nozzle pressure ratio is 3.8, the thrust coefficient of Plan B increases by 8 % over that of Plan A.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2013年第4期772-778,共7页
Acta Aeronautica et Astronautica Sinica
基金
国家自然科学基金(90916023)~~
关键词
二元非对称喷管
可调
数值模拟
风洞试验
推力性能
2D asymmetric nozzle
adjustable
numerical simulation
tunnel test
thrust performance
