张彦军, 段卓毅, 魏剑龙, 雷武涛, 赵轲. 基于风洞试验和数值模拟的超临界机翼雷诺数修正方法研究[J]. 空气动力学学报, 2018, 36(6): 934-940. DOI: 10.7638/kqdlxxb-2017.0213
引用本文: 张彦军, 段卓毅, 魏剑龙, 雷武涛, 赵轲. 基于风洞试验和数值模拟的超临界机翼雷诺数修正方法研究[J]. 空气动力学学报, 2018, 36(6): 934-940. DOI: 10.7638/kqdlxxb-2017.0213
ZHANG Yanjun, DUAN Zhuoyi, WEI Jianlong, LEI Wutao, ZHAO Ke. Research of Reynolds number correction for supercritical wing based on wind tunnel tests and numerical simulations[J]. ACTA AERODYNAMICA SINICA, 2018, 36(6): 934-940. DOI: 10.7638/kqdlxxb-2017.0213
Citation: ZHANG Yanjun, DUAN Zhuoyi, WEI Jianlong, LEI Wutao, ZHAO Ke. Research of Reynolds number correction for supercritical wing based on wind tunnel tests and numerical simulations[J]. ACTA AERODYNAMICA SINICA, 2018, 36(6): 934-940. DOI: 10.7638/kqdlxxb-2017.0213

基于风洞试验和数值模拟的超临界机翼雷诺数修正方法研究

Research of Reynolds number correction for supercritical wing based on wind tunnel tests and numerical simulations

  • 摘要: 结合风洞试验方法和数值模拟,对采用超临界机翼的大型飞机进行雷诺数影响规律研究。对比分析了不同雷诺数下的试验结果和数值模拟结果,在此基础上研究了基于数值模拟结果的雷诺数修正方法,将低雷诺数试验结果向高雷诺数进行修正。修正结果与相应雷诺数试验结果相比,阻力系数相差不超过0.0004,升阻比最大误差约为0.2。针对于力矩系数修正误差问题进行了修正方法改进,改进后的修正误差从0.01降为0.001,表明了修正结果在飞行雷诺数下的适用性。

     

    Abstract: The effects of Reynolds number on aerodynamic characteristics of large aircraft with supercritical wing are studied using wind tunnel test and numerical method. Based on the comparison and analysis between wind tunnel test results and numerical results, the latter are used in the correction of low Reynolds number test results for a high Reynolds number result. The corrected data are compared with the test data for the same Reynolds number. The differences of drag coefficient are less than 0.0004. The maximum difference of lift-drag ratio is approximately 0.2, and the differences of moment coefficient are less than 0.001.

     

/

返回文章
返回