TY - JOUR
T1 - Uncertainty quantification and global sensitivity analysis of transonic aerodynamics about airfoil
AU - Wu, Xiaojing
AU - Zhang, Weiwei
AU - Song, Shufang
AU - Ye, Zhengyin
N1 - Publisher Copyright:
©, 2015, Chinese Journal of Theoretical and Applied Mechanics Press. All right reserved.
PY - 2015/7/18
Y1 - 2015/7/18
N2 - Considering the randomness of Mach number and angle of attack, the non-intrusive polynomial chaos method is employed to analyze the uncertainty and the corresponding global sensitivity indexes of transonic aerodynamics for the NACA0012 airfoil. In the paper, the uncertainty analysis and global sensitivity analysis about the aerodynamic loads, flow field and the aerodynamic coefficients are presented. The results of uncertainty analysis show that the flow characteristics in the shock disturbance region and the boundary-layer separation region are sensitive to the input uncertainties. This is the main reason for the aerodynamic performance fluctuations caused by parameter uncertainties. From the results of global sensitivity analysis, the fluctuations of flow characteristics near the shock wave region are dominated by Mach number. Moreover, the coupling effect between Mach number and angle of attack is significant and cannot be ignored in shock disturbance region. However, this coupling effect is very weak from the results of aerodynamic coefficients.
AB - Considering the randomness of Mach number and angle of attack, the non-intrusive polynomial chaos method is employed to analyze the uncertainty and the corresponding global sensitivity indexes of transonic aerodynamics for the NACA0012 airfoil. In the paper, the uncertainty analysis and global sensitivity analysis about the aerodynamic loads, flow field and the aerodynamic coefficients are presented. The results of uncertainty analysis show that the flow characteristics in the shock disturbance region and the boundary-layer separation region are sensitive to the input uncertainties. This is the main reason for the aerodynamic performance fluctuations caused by parameter uncertainties. From the results of global sensitivity analysis, the fluctuations of flow characteristics near the shock wave region are dominated by Mach number. Moreover, the coupling effect between Mach number and angle of attack is significant and cannot be ignored in shock disturbance region. However, this coupling effect is very weak from the results of aerodynamic coefficients.
KW - Global sensitivity analysis
KW - Non-intrusive polynomial chaos
KW - Stochastic aerodynamic characteristic
KW - Transonic
KW - Uncertainty analysis
UR - http://www.scopus.com/inward/record.url?scp=84938520820&partnerID=8YFLogxK
U2 - 10.6052/0459-1879-14-372
DO - 10.6052/0459-1879-14-372
M3 - 文章
AN - SCOPUS:84938520820
SN - 0459-1879
VL - 47
SP - 587
EP - 595
JO - Lixue Xuebao/Chinese Journal of Theoretical and Applied Mechanics
JF - Lixue Xuebao/Chinese Journal of Theoretical and Applied Mechanics
IS - 4
ER -