Study of Effects of Sweep on the Flutter of Cantilever Wings

摘要: An experimental and analytical investigation of the flutter sweptback cantilever wings is reported. The experiments employed groups swept back by rotating shearing. angle sweep range from 0 degree to 60 degrees Mach numbers extended approximately 0.85. A theoretical analysis air forces on an oscillating wing high length-chord ratio developed, approximations inherent in assumptions are discussed. Comparison with experiment indicates that developed present report satisfactory for giving main effects sweep, at least nearly uniform moderate ratios.