| The analysis of the time independent mean flow in the combustion chamber of a rotating PAM-D rocket motor is presented. The flow field is modeled using the Navier-Stokes equations for a viscous, incompressible, Newtonian fluid in an axisymmetric, non-inertial coordinate system. The resulting nonlinear differential equations are solved using the finite element method and a Newton-Raphson iteration technique with analytically derived derivatives.; Streamlines are shown for nonrotating cases with Reynolds numbers from 0.8 to 15.0 and for rotating cases with Rossby numbers of 0.8 and 0.4. The analysis shows that the negative pressure gradient caused by the flow converging toward the nozzle effectively suppresses the flow separation in the aft end of the cavity and that the axial flow originating at the head end precludes the formation of a narrow vortex core along the axis.; Source code for the analysis program is included. |
