Distributed Electric Propulsion (DEP) systems integrated with airframes offer significant potential for future aircraft but introduce complex aerodynamic interactions. This paper numerically investigates these interference effects for a wing with multiple integrated ducted fans using a Computational Fluid Dynamics (CFD) approach based on the Momentum Source Method (MSM). The MSM implementation was validated against experimental data for the NASA D-995 isolated ducted fan, demonstrating good agreement with experimental thrust predictions (mean deviation of approx. 8.4%). Simulations of the wing-integrated configuration revealed significant Boundary Layer Ingestion (BLI), causing notable inlet flow distortion. The study systematically examined the impact of varying vertical distances (wing-to-fan) and lateral spacing (fan-to-fan) on the flow field and pressure distributions. Results show that closer vertical integration intensifies BLI effects. Critically, the influence of lateral spacing on interference patterns and BLI was found to be non-monotonic, suggesting an optimal spacing may exist rather than a simple trend. The observed modifications to the wing pressure distribution highlight potential avenues for synergistic aerodynamic design. This work provides valuable insights into propulsor-airframe integration challenges and confirms the MSM’s utility for efficiently analyzing such complex configurations.