With the aim to reduce the global carbon emission, the hydrogen-powered aircraft become the future focus of the ever growing aviation industry. Ditching or the emergency landing of the aircraft on water is an inevitable aspect especially on the transoceanic route. Due to the highly flammable nature of hydrogen as well as the position of liquid hydrogen tanks on the aircraft, the reliable estimation of hydrodynamic loads is extremely crucial so that the structural limit of the aircraft frame is not exceeded in the event of ditching. Besides accident investigations and scaled model experiments, numerical simulations are widely used to investigate ditching behavior. Investigations are typically split into four subsequent chronological phases, i.e.,an approach, impact, landing and floatation (evacuation) phase. In particular, the emerging loads and aircraft dynamics are analyzed during the impact and landing phase. The ditch simulation, based on the momentum theory by von Karman and Wagner, is used for the present research. The method is the low-fidelity hybrid approach which is analytical with empirical corrections. It supports extensive sensitivity studies, optimizing aircraft's approach conditions and serves as simulation based tool for design verification. In this study, the results obtained from rigid aircraft simulations with the tool ditch are presented for a wide range of input parameters which include (a) approach phase parameters, e.g. the initial horizontal and vertical velocities and pitch angle as well as (b) configuration parameters, e.g. mass, center of gravity and moment of inertia. The results also aim to provide guidance and recommendations for the ditching procedure, its limitations, and optimization potential, as well as critical design and procedural parameters.