摘要
为提高大型飞机风洞试验时的支撑系统刚度、降低支撑气动干扰以及实现真实船尾后体流动的模拟,在2.4米跨声速风洞中建立了条带悬挂支撑试验系统。主要包括专用试验段、条带支撑机构、控制系统、天平设备、标模及半弯刀尾支撑机构研制等六部分。系统研制成功后,在2.4米跨声速风洞中开展了流场调试及标模试验,分别采用风洞试验和数值模拟方法获取了条带悬支撑的干扰量。在某飞机高速风洞试验中,采用条带支撑系统,获得了飞机模型的气动特性,并与尾撑试验结果进行了对比。以条带支撑为辅助支撑,得到了尾支撑干扰量,与腹撑试验结果进行了对比。研究结果表明,条带悬挂支撑系统具备型号应用条件,同期重复性精度高,在-2°≤α≤2°范围内,重复性精度满足σCL≤0.0012,σCD≤0.00013,σCm≤0.0005,标模试验结果与国外风洞试验相关性较好;条带支撑干扰试验结果与数值模拟吻合较好,低亚声速时支撑干扰量较小,在-4°≤α≤10°范围内,M=0.6时的支撑干扰量ΔCL≤0.005,ΔCD≤0.0008,ΔCm≤0.005。
The vane cable suspension support system in the CARDC 2.4m Transonic Wind Tunnel was successfully developed for the sake of high stiffness,less support interference and fully simulation of a boat tail in this paper,the system includes test section,support system,control system,balance,standard model and attack angle mechanism.The flow filed calibration and standard model tests were conducted,interference of the support was obtained utilizing numerical and experimental methods.Aerodynamic characteristics of a typical airplane were obtained using this vane cable suspension support system,and were compared with the results obtained with single sting support.The interference of single sting was also achieved by the utilization of the suspension support and was compared with that of blade support.Results indicated that the vane cable suspension support system is successful,the short term repeatability of standard model is high,which meetsσCL≤0.0012,σCD≤0.00013,σCm≤0.0005 while-2°≤α≤2°.Interference of the vane cable suspension support system is low at subsonic speed,which meetsΔCL≤0.005,ΔCD≤0.0008,ΔCm≤0.005 while M=0.6and-4°≤α≤10°.
出处
《空气动力学学报》
CSCD
北大核心
2016年第3期354-361,共8页
Acta Aerodynamica Sinica
基金
空气动力学国家重点实验室基金(JBKY15020201)
关键词
条带悬挂支撑
Ty154标模
支撑干扰
风洞试验
vane cable suspension support
Ty154standard model
support interference
wind tunnel test
