Course centers on developing fixed-wing UAVs with enhanced aerodynamic capabilities. Design uses the concept of Circulation Control (CC) that takes advantage of the Coanda effect and has been proven to be the most effective active flow control method for wing lift enhancement and wing weight reduction at low Mach numbers when compared to conventional flaps and slats that are used as augmentation devices. The idea is to design Circulation Control Wings (CCWs) using a mechanical high lift system, which allows for tangential blowing over a rounded or near rounded trailing edge (of the wing) to yield high lift augmentation with low value mass flow rates. The jet that comes out of the slot, which is located at the trailing edge of the CCW remains attached to the surface and moves the separation point around the trailing edge toward the lower surface of the wing resulting in lift augmentation. This type of aircraft is shown to have enhanced performance, reduced take-off runway, delayed stall and increased payload during cruise flight. A comprehensive methodology is presented along with design details to develop a Class I fixed-wing UAV that include system and parameter identification and power/energy optimization. This is followed by a nonlinear controller design methodology, as such systems constitute a family of nonlinear ones with unstructured uncertainties and time-varying aerodynamic coefficients. Experimental results and real flight tests demonstrate applicability and usability of the proposed frameworks. Topics to be covered are: principals of fixed wing UAV aerodynamics, Circulation Control fundamentals, design, development, wind tunnel (WT) experimental testing, validation and verification (V&V) and performance evaluation of CCW based UAVs, and nonlinear controller design.