摘要
在跨声速范围内,战斗机内埋式武器弹舱流场具有强烈的非定常特征。为获得准确的试验数据,需要对我国唯一的2m量级以上的2.4m×2.4m引射驱动式跨声速风洞开孔壁面试验段进行适应性改造。通过采用计算流体力学(CFD)数值模拟方法对引导风洞试验段设计方案进行评估优化,以获得最佳设计结果。与采用马赫数为1.4的喷管和开孔壁面试验段时的试验结果相比较,文中采用的开孔试验段壁板边界条件能获得较为准确的流场特性。对设计方案的数值研究结果表明,前过渡段的收缩与扩张降低了试验段气流质量,后过渡段引射缝开度明显影响分离特性,对前过渡段开孔率分布规律的优化使试验段流场均匀性达到了试验要求。
The flow field related to the interior weapons bay of a combat aircraft is associated with strong unsteadiness effects in the transonic range. The perforated test section of a 2.4 m× 2.4 m injection driven transonic wind tunnel, whose test section caliber is China＇s only one larger than 2 m, is redesigned so as to obtain more accurate experimental data. Stri- ving for the best design, attempts are made using computational fluid dynamics （CFD） analysis to evaluate and optimize the preliminary design project of a pilot wind tunnel. The boundary conditions of the perforated test section wall are validated by comparing with the experiment results at Mach number Mat = 1.4, and then used for simulations of several projects. The current research reveales that the flow characteristics are greatly influenced by the entrance transition section and outlet tran- sition section. The contraction and expansion of the entrance debase flow quality. The attitude of the injection flaps deter- mines the size of the separation area. Then different models using different open-area ratios of perforated wall at entrance are investigated based on the numerical results. Desired flow quality is obtained when the transition section adoptes reason- able open-area ratios.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2012年第6期1014-1019,共6页
Acta Aeronautica et Astronautica Sinica
基金
空气动力学国家重点实验室基金(JBKY11040401)~~
关键词
跨声速风洞
试验段
开孔
数值模拟
气动设计
transonic wind tunnel
test section
perforation
numerical simulation~ aerodynamic design
