INVESTIGATION OF A SLAT IN SEVERAL DIFFERENT POSITIONS ON AN NACA 64A010 AIRFOIL FOR A WIDE RANGE OF SUBSONIC MACH NUMBERS

摘要

An investigation of the two-dimensional aerodynamic characteristics of an NACA 6UA010 airfoil with a slat has been conducted in the Mach number range from 0.25 to 0.85, with a corresponding Reynolds number range from 3.4 million to 8.1 million. Two families of slat positions were investigated, one with the slat leading edge extended forward along the airfoil chord line, and the other with the slat extended forward and displaced below the chord line.nThe results indicate that for section lift coefficients up to 0.6> the airfoil with the slat retracted generally was aerodynamically superior to any of the other airfoil-slat arrangements investigated. The drags with the slat nose on the extended chord line were only slightly higher than the drag with slat retracted, whereas displacing the slat nose below the chord line markedly decreased the drag-divergence Mach number. Above 0.7 section lift coefficient and at the higher test Mach numbers, the best results were obtained with the slat nose on the extended chord line of the airfoil.