CHN-T1标模大型低速风洞试验结果相关性分析

为满足型号研制的试验数据质量需求，进一步开展CFD验证与确认工作，中国空气动力研究与发展中心建立了大展弦比运输机高低速统一标模体系。为获得可靠风洞试验数据，使用设计加工的第一个运输机标模CHN-T1（1:6.4，翼展4.667m）在FL-13风洞和DNW-LLF风洞进行了试验。同一构型下，前者试验雷诺数为1.4×106~2.5×106，后者试验雷诺数为1.4×106~3.2×106。模型在FL-13风洞中通过TG1801A内式六分量天平与大迎角支撑机构相连，在DNW-LLF风洞中则通过W616天平与尾撑机构相连。两风洞均测量了模型力和力矩。风洞试验数据差异评估包括重复性、气动特性和雷诺数影响。结果对比表明:标模在不同风洞试验中的升力线斜率相差很小；设计升力点附近（Ma=0.78，C_L=0.5）阻力系数相差0.0004，试验数据一致性较好；雷诺数对标模气动特性影响符合预期。

Correlation analysis of large low speed wind tunnel test on CHN-T1 calibration model

China Aerodynamics Research and Development Center (CARDC) established a uniform large aspect ratio transport aircraft calibration model system for high and low speed wind tunnels to fulfill the data quality requirements of aircraft type development and CFD validation and confirmation. To acquire reliable wind tunnel data, CARDC tested the first self-developed transport calibration model CHN-T1 (1:6.4, 4.667m wing span) in FL-13 wind tunnel and DNW-LLF wind tunnel at chord Reynolds number from 1.4 to 2.5 million in FL-13 wind tunnel and from 1.4 to 3.2 million in DNW-LLF wind tunnel for the same configuration. CHN-T1 model was mounted on a TG1801A six-component strain-gauge internal main balance connected to the large angle of attack (AOA) support mechanism in FL-13 wind tunnel and on a W616 internal main balance connected to a sting support in DNW-LLF wind tunnel. Both of the force and moment data were obtained in both facilities. Tunnel to tunnel variations including repeatability, aerodynamic characteristics and Reynolds effect have been assessed. Results comparison shows that slop of lift curve (C_Lα) varies very little and drag coefficient (C_D) is of a difference of 0.0004 around the design point with Ma=0.78 and lift coefficient (C_L)=0.5. Test data indicates good agreement. Reynolds number effect on CHN-T1 calibration model aerodynamic characteristics follows the expected trends.