Abstract
It is necessary to improve the correlation between CFD and EFD through the correction of EFD results and validation of CFD method, thus investigating the aerodynamic characteristics of supercritical airfoil perfectly. In this study, NASA SC (2) -0714 airfoil is numerically simulated and compared with NASA corrected experimental results to validate the CFD method. The Barnwell-Sewell method is applied to correct sidewall effects for experimental results of typical supercritical airfoil CH obtained in NF-6 wind tunnel. It is shown that there was large disparity between CFD and uncorrected EFD results, while CFD and EFD compared well after correction. The CFD method is validated and the Barnwell-Sewell method is feasible for sidewall effects correction. The correlation of EFD and CFD improved after the correction of EFD results and validation of CFD method.
Highlights
Aerodynamic characteristics of airfoil which reflect the basic performance of an aircraft could be obtained in wind tunnel test
It is necessary to improve their correlation through the correction of EFD results and validation of CFD method, investigating the aerodynamic characteristics of supercritical airfoil perfectly
The Barnwell-Davis-Moore method is limited for the correction of attack angle, which is unfeasible for supercritical airfoil (Hess et al, 1989)
Summary
Aerodynamic characteristics of airfoil which reflect the basic performance of an aircraft could be obtained in wind tunnel test. There is three-dimensional flow around the test model and the blockage at high attack angle is unacceptable, which would make results unreliable for the supercritical airfoil wind tunnel test; there is shock-induced separation on the upper surface of supercritical airfoil which is difficult to simulate through numerical method. It is necessary to improve their correlation through the correction of EFD results and validation of CFD method, investigating the aerodynamic characteristics of supercritical airfoil perfectly.
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