Magnus Effect on Spinning Bodies of Revolution.
Abstract:
A numerical finite difference method is developed to solve the three dimensional laminarturbulent boundary layer equations on a spinning body of revolution at an angle of attack in supersonic flow. Influence of asymmetric transition and the presence of mixed boundary layers is considered to predict Magnus forces and moments. Several contributions to the Magnus effects are considered. These include asymmetric boundary layer displacement thickness, centrifugal pressure, and primary and cross flow wall shear stresses. Boundary layer structure defined by asymmetric transition is shown to critically influence the aerodynamic forces and moments on bodies of revolution. Important variables in the flow field are identified by considering variations of spin rate, Mach number, angle of attack and length of the body. Comparisons are made with experimental data and other theoretical analyses. Author