A coupled aerodynamic framework is developed that combines an axisymmetric potential-flow solver around a body of revolution with an integral boundary-layer model and an actuator-disk representation of the propulsor. The actuator disk is prescribed through a radial pressure jump, and a slipstream correction model is used to obtain a consistent combined velocity field inside and outside the wake. Loss-related behaviour is quantified using power-flux measures evaluated at freestream, upstream, and downstream stations, together with wake non-uniformity indicators and mixing-loss metrics based on radial shear in the developed slipstream.

Three families of radial loading are studied at equal thrust: a uniform pressure-jump baseline, a stepwise (multi-disk) redistribution, and an approximately elliptical. Results show that redistributing loading toward the ingested boundary-layer region can reduce downstream power-flux deficits and weaken radial velocity gradients, indicating reduced mixing losses compared with the uniform baseline. The analysis highlights a trade-off between concentrating thrust in low-momentum inflow and maintaining a smooth slipstream profile to minimise shear-driven dissipation.

Finally, an inverse blade-design procedure is presented to convert the prescribed actuator-disk loading into chord and twist distributions using a drag-aware blade-element–momentum formulation with airfoil polar data. The resulting geometries provide blade-level interpretations of the disk-level loading strategies and demonstrate how BLI-driven loading redistributions lead to propeller designs that differ substantially from conventional uniform-inflow propellers.

The use of plasma actuators for active flow control presents an interesting option for the design of an aircraft. Plasma-actuated systems boast the opportunities of having facilitated maintenance, increased operational efficiency, and a decreased noise profile, with minimal impact on general performance. Yet, due to the novelty of the technology, the exact implementation of a 100% plasma-controlled drone is yet to be done. Group 16 was tasked with designing an unmanned aerial vehicle (UAV) which omits conventional mechanically-actuated control surfaces, and instead uses plasma actuators. This report explores the various technical and non-technical design facets of the Plasma-actuated Unmanned Light Surveillance and Eco-friendly Drone (PULSE Drone). Due to the inherent novelty in the design stages, this paper aims to explain the current PULSE Drone design and its approach such that it becomes a benchmark for future development. From the depth of explanations, this paper becomes a relevant source for future projects aiming to incorporate plasma actuators.