An experimental wing-flutter investigation was conducted in the Langley transonic blowdown tunnel, which is equipped with a slotted test section, in order to determine the correlation between transonic-wind-tunnel and free-fall flight flutter results. Flutter was obtained in this variable density wind tunnel at several Mach numbers between 0.84 and 1.16 for two unswept, rectangular wings of aspect ratio 7° 38 at 0° angle of attack. These wings were scaled models of wings which had fluttered in the course of free-fall flight tests. The very good agree¬ment between the wind-tunnel and flight flutter test results shows the feasibility of conducting flutter tests in transonic wind tunnels with slotted test sections.
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