A copy of this work was available on the public web and has been preserved in the Wayback Machine. The capture dates from 2017; you can also visit the original URL.
The file type is application/pdf
.
Reynolds Number Effects Investigation of Supercritical Airfoil Based on EFD and CFD
2013
Research Journal of Applied Sciences Engineering and Technology
This study aimed to investigate the transonic Reynolds number effects of supercritical airfoil by EFD and CFD method. An experiment was conducted in NF-6 wind tunnel, to obtain the pressure distribution and aerodynamic coefficients of a typical supercritical airfoil through pressure measuring, with Reynolds numbers varied from 3.5×10 6 to 1.0×10 7 per airfoil chord, Mach numbers from 0.6 to 0.8, angles of attack from 0° to 8°. Also, flows over the supercritical airfoil were numerically studied;
doi:10.19026/rjaset.6.3441
fatcat:t3zotefunvcqncfdzmbu6dozym