Implementation and validation of an engine nacelle boundary condition in Edge 3.2

The implementation of a boundary condition which enables the coupled computation of air flow in and out of engine nacelles is described and tested. The boundary condition is implemented into the hybrid solver Edge. User input is limited to specification of the pressure and temperature ratio at the nacelle exhaust. Two test cases are computed: a simple nacelle and a business jet fitted with two turbofan engines. Satisfactory results are obtained in both cases.