The report describes the development of a performance model for a precision guided mortar munition (PGMM) with deployable wings. Most of the material, however, is generally applicable to missiles with essentially cylinder symmetric configuration which are operated in skid-to-turn mode. Topics covered are modeling of aerodynamic and flight mechanical characteristics using so called handbook methods, and performance attainable with a simple linear controller. Particular attention is devoted to development of a reduced dynamics model based on two sets of linearized pitch plane dynamics, and the assumptions and simplifications that are made in this process. The vehicle used as design example (PGMM) is a subsonic glider with moderate turn performance and relatively low glide ratio where the goal of the aerodynamic design is primarily to enhance range (compared to ballistic flight) and add maneuvering capabilities to hit slowly moving targets.