Rotorcrafts are extensively used in battle and rescue operations, and often this requires them to function effectively in confined environments. During these operations, the rotorcraft operates near to the ground, and other vertical obstacles present nearby. A UAV or MAV operating inside a building or a helicopter landing on a ship deck are examples of such scenarios. Rotorcrafts when hovering near the ground experience an increase in thrust, this phenomenon is referred to as ground effect. Extensive research has been done on ground effect over the years. One of the significant areas of interest in rotorcraft research is the interaction of the rotor wake with nearby structures (ground and walls). The aerodynamics of a rotor near to ground (IGE) is different when compared to out of ground (OGE) condition. Most of the works in the literature is based on theoretical analysis, and there exist some gaps in the current state-of-the-art pertaining to ground effect. This research proposal outlines the investigation of two such aspects - evaluation of the effect of ground on a hovering rotor inflow distribution through experimental and computational analysis and the effect of oscillating ground on the roll, pitch moments and radial inflow distribution. The study focuses on the effect of diverse landing conditions encountered by helicopters on their performance, specifically - inclined ground and dynamic ground. These conditions cause an asymmetry in the wake-field and consequently affects the forces and moments experienced by the vehicle. This proposal -with the aid of computational and experimental analysis and advanced dynamic inflow models- explores the possibilities of modelling the unsteady loads to formulate an exhaustive correction factor for this effect. In addition, this study can be extended to the helicopters hovering over ship decks during landing or take-off at sea, where they are subjected to unsteady loads resulting from the obstruction of the wake by the heaving/oscillating deck and ship superstructure.