Multidimensional parametric study of a propulsive fuselage concept using openfoam

Aircraft concepts, which utilize boundary layer ingestion as a means to increase airframe and propulsion system integrated performance, such as propulsive fuselage concepts, have been the subject of many studies in the recent past. High fidelity numerical and experimental methods have been employed to optimize fuselage and propulsor geometries and performance characteristics. However, some of the fundamental principles that relate the physical shape of a fuselage-propulsor to the potential benefit of boundary layer ingestion are still not fully understood. The presented methodology serves as a tool to investigate the effect of geometrical propulsor parameters and fuselage-propulsor fan pressure ratio on the performance of a propulsive fuselage aircraft concept. For this purpose, a method for the systematic design space exploration of a fuselage-propulsor configuration is presented and applied in a 2D axisymmetric CFD study.