Hypersonic glide vehicles are typically launched by booster rockets and glide through the atmosphere at speeds exceeding five times the speed of sound. Due to their flexible manoeuvrability and high speed they are considered difficult to defend against, using current missile defense systems. The purpose of the research described in this report is to characterise the performance, in terms of manoeuvrability, of hypersonic glide vehicles used for weapon delivery. A typical concept for a hypersonic glide vehicle called Common Aero Vehicle (CAV-H), launched on an intercontinental range booster, is used as a basis for the analysis. A trajectory optimisation problem is formulated as an optimal control problem, for a number of different scenarios, to find the maximum downrange and crossrange trajectories as well as the reachable ground impact area, often called the footprint. The optimisation problem is solved by adopting an open source optimal control software package called PSOPT, to transcribe the flight dynamics using direct collocation methods to a set of nonlinear constraints and solve the arising nonlinear programming problem. The results show that the studied hypersonic missile configuration can be used for striking targets at long-range distances beyond 8000 km downrange for a number of different impact angles and speeds. Even targets located beyond 3300 km crossrange can be hit provided a downrange target distance of around 5000 km. The manoeuvrability of a hypersonic glide vehicle can be used for deception, by initially launching it in one direction, and then turning to hit a target located in another direction. Depending on where along the trajectory the manoeuvring starts, the reachable ground impact area is reduced. The hypersonic glide vehicle can also be manoeuvred to avoid certain areas because of e.g. geopolitical sensitivity, or because of threats from adversary defense systems. Due to the large turning radius, there are restrictions in how close to a no-fly zone manoeuvring must commence.