Design integration and noise studies for jet STOL aircraft. Task 7B: Wind tunnel investigation of a 14-percent-thick airfoil with upper surface blowing at high subsonic Mach numbers

An exploratory wind tunnel test has been conducted at Mach numbers from 0.60 to 0.80 to investigate the effects of nozzle geometry and upper surface blowing on the aerodynamic characteristics of a 14-percent-thick airfoil. Measured data included lift, drag, pitching moments, surface pressures, and nozzle thrust.