Abstract
The effects of boundary conditions of computational analysis on edgetone phenomena are investigated. Two-dimensional compressible Navier-Stokes equations are solved with high-order compact finite difference scheme and Runge-Kutta scheme. The edgetone phenomena under various nozzle lip-thicknesses and jet profiles are computed. Edgetone phenomenon becomes stronger with increasing nozzle lip-thickness. This effect seems to be explained as larger lip-thickness emphasizes feedback-loop. Besides the change of jet-profile under the same maximum velocity affects edgetone frequency, strength and stage. These effects are due to the difference of averaged velocity. The change of jet-profile under the same averaged velocity affects frequency of the edgetone. This effect is caused by the difference of convective velocity of disturbance with Powell's feedback-loop theory.
