A Velocity Based Boundary Element Method with Modified Trailing Edge for Prediction of the Partial Cavities on the Wings and Propeller Blades

摘要

This paper presents a new velocity based boundary element method for calculation of the partial cavities on the wings and propeller blades. The fully correct mathematical formulation of the problem about cavitating bodies is characteristic feature of the developed method and numerical algorithm. The special algorithm of Modified Trailing Edge (MTE) is used for definition of the lifting (circulation) part of the flow. MTE tool allows the approximate accounting for viscous effects on lift and pressure distribution. The miscellaneous cavity closure model is recommended for calculation. The prediction of the cavity patterns is performed using Iterative Cavity Alignment (ICA) procedure with Free Cavity Length (FCL). The results of the test calculations and comparisons with experimental data are given in the paper.