Abstract
Recent research has focused on the design of aircraft that provide significant reductions in emissions, noise, and fuel usage. One of the strategies to increase fuel efficiency is to leverage the potential structural weight saving available by using novel configurations such as the truss-braced wing. The Boeing Company recently tested the Subsonic Ultra-Green Aircraft Research Truss-Braced Wing wind-tunnel model in the NASA Langley Research Center Transonic Dynamics Tunnel. This test resulted in a wealth of accelerometer data that are indicative of the dynamic behavior of the model near flutter onset. For the truss-braced wing model test, the flutter onset was preceded by a large Mach number/dynamic pressure area in which the model displayed wing/engine nacelle aeroelastic limit-cycle oscillation. This paper analyzes those limit-cycle oscillation data to provide additional insights into the aeroelastic behavior of the model. Spectral analyses indicate the coalescence of several wing modes into a single-frequency limit-cycle oscillation. The mapping of limit-cycle oscillation at that frequency at progressive amplitudes indicates a substantial variation in onset with angle of attack. Spectral analysis also provides evidence of nonlinearity in both the aerodynamic and structural dynamics.
Published Version
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