Investigation to optimize the passive shock wave-boundary layer control for supercritical airfoil drag reduction

摘要

The optimization of passive shock wave/boundary layer control for supercritical airfoil drag reduction was investigated in a 3 in. x 15.4 in. Transonic Blowdown Wind Tunnel. A 14 thick supercritical airfoil was tested with 0, 1.42 and 2.8 porosities at Mach numbers of .70 to .83. The 1.42 case incorporated a linear increase in porosity with the flow direction while the 2.8 case was uniform porosity. The static pressure distributions over the airfoil, the wake impact pressure data for determining the profile drag, and the Schlieren photographs for porous surface airfoils are presented and compared with the results for solid-surface airfoils. While the results show that linear 1.42 porosity actually led to a slight increase in drag it was found that the uniform 2.8 porosity can lead to a drag reduction of 46 at M = .81.