The hybrid upper surface blowing concept consists of wing-mounted turbofan engines with a major portion of the fan exhaust directed over the wing upper surface to provide high levels of propulsive lift, but with a portion of the fan airflow directed over selected portions of the airframe to provide boundary-layer control. NASAsponsored preliminary design studies identified the hybrid upper surface blowing concept as the best propulsive lift concept to be applied to the Quiet Short-Haul Research Aircraft (QSRA) that is planned as a flight facility to conduct flight research at low noise levels, high approach lift coefficients, and steep approaches. Data from NASA in-house and NASA-sponsored small-and large-scale wind-tunnel tests of various configurations using this concept are presented. Nomenclature b = wing span BLC = boundary-layer control CL = lift coefficient, L/qS Cia = 0 = h'ft coefficient at zero angle of attack CL^ ~ 2. ' = lift coefficient at an angle of attack of -2 ° CL^ax = maximum lift coefficient C/ = rolling-moment coefficient, rolling moment/qSb Cn = yawing-moment coefficient, yawing momQnt/qSb CT = thrust coefficient, gross thrust/qS C/z = blowing momentum coefficient, gross thrust from BLC nozzle/qS L -lift Pl£IP^ = pressure ratio, total pressure at engine nacelle exit/tunnel static pressure q = freestream dynamic pressure S = wing area V = velocity W/S = wing loading a = angle of attack 6/r = deflection angle of thejrailing-edge flap