Future projections indicate that continued population growth will lead to further expansion and densification of urban environments, thereby increasing transportation demands and associated challenges. In this context, Urban Air Mobility (UAM) has emerged as a promising solution, enabling new intra- and inter-urban transportation services through the use of Vertical Take-Off and Landing (VTOL) aircraft, more precisely configurations such as lift and cruise tiltrotors which combine the hovering capability of conventional helicopters with the cruise speed and range of fixed-wing aircraft by means of tilting propulsion mechanisms. Optimizing the aircraft design process is essential to reduce overall development time and cost. During the conceptual design phase, propeller design methodologies commonly reported in the literature rely on vortex-based approaches or actuator disk theory to estimate the main propeller characteristics. However, the accuracy of these methods strongly depends on the inflow angle and operating conditions, with discrepancies increasing as the inflow angle and advance ratio grow. This paper introduces an analytical model to predict propeller thrust at a 90° inflow angle (pure lateral flow), based on a correction of the thrust under perpendicular flow conditions and the propeller geometry evaluated at 75% span. The approach relies on local velocity and angle of attack estimations derived from classical Blade Element Momentum Theory (BEMT). The propeller lift coefficient is obtained by representing the blades as thin airfoils, with an additional correction to account for stall effects at high angles of attack, while the drag coefficient is calculated based on the known thrust values. The induced velocity, required for local flow calculations, is estimated from known thrust values and discretizing the propeller disk according to the number of blades. This capability is particularly relevant for modeling lift and cruise tilt rotor configurations cruise phase during early design stages while maintaining minimal computational cost. The proposed model is validated against wind tunnel measurements for several propellers tested at different global pitch angles, demonstrating the applicability of the developed formulation for blades with twist angles up to 16°.