Tests at Subsonic Speeds on a Half-Wing with a Fan Engine Nacelle
نویسندگان
چکیده
SUMMARY Flutter tests have been made on a half-wing model with a fan-engine nacelle attached by a pylon at an inboard section. The model was nominally rigid and flexibilities in pitch and roll were introduced at the root. Measurements were made of the flutter characteristics of the model at Mach numbers of 0.6 and 0.8 over a range of dynamic pressures using three different methods of analysis. The nacelle was replaced by a narrow 'pencil' of equivalent inertia in order to assess the effects on the flutter characteristics of the aerodynamic forces on the nacelle. It is shown that these forces modify significantly the aeroelastic behaviour of the wing-nacelle system. The tests were made in conjunction with the Office National d'Etudes et de Recherches Agrospatiales, and were part of a larger investigation which included static and oscillatory pressure measurements on the wing.
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