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TRANSONIC FLUTTER TESTS OF A HIGHLY SWEPT ARROW WING WITH AND WITHOUT SIMULATED TRAILING-EDGE-MOUNTED ENGINE MASSES
NATIONAL AERONAUTICS AND SPACE ADMINISTRATION WASHINGTON D C
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Transonic flutter tests were made for three series of cantilevered semispan wing models which had arrow planforms and leading-edge sweep angles of 72.5 degrees. The first series were basic wing panels the second series carried simulated engine masses and nacelles located at 34.9, 55.8, and 76.6 of the semispan the third series carried only lightweight nacelles. The mass of each simulated engine was approximately 41 of the basic wing-panel mass. At Mach numbers below 0.975, the addition of the engine masses increased the flutter dynamic pressure of the basic wings the nacelles do not affect the flutter boundary of the basic wings in this Mach number range. At Mach numbers above 1.05 the flutter boundary for the wings with engine masses and nacelles was higher than the boundary of the basic wings, but below the boundary for the wings with only lightweight nacelles. Author
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