There is a continuing need to explore and expand the design space for all categories of aircraft. With reference to UCAV’s and related HALE aircraft, stealth considerations impose sweep and taper constraints. At low speeds, high incidence is required for high CL. Flow may deteriorate and pitch-up may occur and this will limit the design capability. On flying wing type planforms, conventional means (stabilising tailplanes) are not usually available to prevent this type of behaviour. We have previously carried out a fair amount of work on Leading Edge Vortex Flaps (LEVF) on various configurations (moderate to high sweep), experimentally and theoretically. Such devices can be used in sympathy with the onset of separated (vortical) flow to turn a possibly major disadvantage into a distinct advantage. They can be used towards reducing drag or enhancing CLmax. The applicability is to Flying wings / oblique wings and conventional wings or where high lift may be limiting. Incorporation may be over the whole or part span. The LEVF could also be classed as part of the morphing scene. Some of the early ideas on LEVF may be relevant and could be adapted to conventional and unconventional UCAV wings. Incorporation on stealthy wings needs careful consideration. It may be that we are restricted to hinge-lines / break-lines over the upper surface. Over the years, we have developed a series of design and analysis methods that can be used with much more confidence when considering LEVF on UCAV type configurations. The techniques have proved easy to use. The design process is iterative and allows modifications to geometry and aerodynamic characteristics as required at any stage. Favourable characteristics of the configuration can be enhanced whereas those that are not beneficial can be minimised or avoided as the design progresses. We have considered two planforms, each applicable to high speed UAV/UCAV operation. One has straight swept LE (Λ=42.8, AR=3.71), the other has LE kink (Λ=54.5/34.6, AR=3.61). The latter is similar to current Blended Wing Body (BWB) concepts. Panel methods have been used to rapidly define the wing and LEVF geometries. The aerodynamic performance of the designed configuration has been verified using Euler analyses and good correlation has been obtained. Several avenues of further work and development have arisen.