An axisymmetric nacelle and turboprop inlet analysis including powersimulation

Abstract

An axisymmetric nacelle and turboprop inlet analysis is presented. The transonic small disturbance potential equation is solved in nonconservaiive form by means of column relaxation on a Cartesian mesh. Exact surface boundary conditions are implemented to account for the influence caused by the strong interatcion of neighboring bodies. The Kutta condition is included so that flow-through as well as sting mounted configurations can be simulated. The analysis includes an actuator disk model to simulate power input for either ducted fans or propellers. The actuator disk formulation specifies the necessary jump conditions both at the disk and along the jet plume or propeller wake slipstream. Comparisons are made with exact full potential solutions and with wind tunnel data.