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25 percent 9.3-percent-thick supercritical airfoil a.deg Cq Cm angle of attack angle-of-attack range BPR 10.0 configurations BPR 10.0 engine BPR 6.2 configurations bypass ratio Cf Cm Concluded Continued data show deflected and leading-edge due to spoiler Effect of horizontal-tail Effect of spoiler Effect of wing engine simulators engine-out rolling externally blown flap Figure 43 flaps deflected full-span fuselage center line horizontal tail horizontal-tail incidence angle inboard engine engine increasing thrust coefficient landing configuration landing flap configurations leading-edge slat configuration left inboard engine left outboard engine longitudinal aerodynamic characteristics longitudinal data maximum lift coefficient maximum untrimmed lift mean geometric chord model with flaps NASA NASA TN outboard engine engine power recovery quarter-chord Root chord shown in figure slat chord supercritical airfoil wing symmetrical power T-tail and low take-off configuration take-off flap thrust area U.S. Customary Units untrimmed lift coefficients Wind-Tunnel wing chord wing leading-edge slat