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RESULTS OF WIND TUNNEL TESTS OF A FULL SCALE, FUSELAGE MOUNTED, TIP TURBINE DRIVEN LIFT FAN. VOLUME 3
GENERAL ELECTRIC CO CINCINNATI OH
Results are reported of wind-tunnel model tests of a tip-turbine- driven lift fan X353-5 mounted in the fuselage of a full-scale model. Longitudinal stability margin with fan operating was increased. STOL performance was essentially unchanged. Lift loss due to throttling the fan was very sensitive to height above ground. Pitching moments longitudinal trim requirements in ground effect decreased at low velocity ratios, but increased at high velocity ratios because of tail downwash increase. The fan flow decrease was accompanied by hub stall by a high static pressure ratio across the rotor. Modifications to test equipment and new instrumentation are discussed.
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