Flutter Phenomenon and Safety Implications in Transonic Flow

Abstract

As advancements in aircraft manufacturing technology persistently elevate the boundaries of flight speed, challenges emerge when aircraft velocities verge on sonic speeds. Notably, empirical observations have highlighted instances of pronounced vibrations and, in extreme cases, structural failures, casting shadows over flight stability and safety. This research endeavors to dissect the ramifications of shock waves and flutter phenomena, precipitated by fluid discontinuities during supersonic flight, on the overarching safety of aircraft. Methodologically, the study delineates a series of simulation protocols, commencing with the derivation of simplified functions representing the aircraft's 2D contour, followed by error function computations, and finally, using the finite difference method in conjunction with the successive over-relaxation (SOR) iterative technique to model the aircraft's velocity distribution. Preliminary findings indicate that for β values spanning 0.1, 0.15, and 0.175, the surrounding airflow retains its continuity and stability, with the Mach number's rate of change exhibiting a decelerating trend. Conversely, at a β threshold of 0.2, the airflow descends into turbulence, manifesting in erratic Mach number fluctuations. Such fluidic discontinuities underscore potential threats to the aircraft's flight safety, necessitating further exploration and mitigation strategies.