Estimation of Induced Velocity of Helicopter Rotor Blade for Controlling and Stability

This paper presents an analytical and simulated investigation of the helicopter rotor blade employing the NACA 0012 airfoil. The simulations are conducted using the CFD ++ software. A crucial parameter for stress and pressure analysis of underlying structures is the induced velocity resulting from the downwash of the helicopter rotor. This induced velocity is intricately linked with the vertical climb velocity observed during the helicopter's ascent phase. The combination of induced velocity and vertical climb velocity contributes to the pressure distribution on objects within the downwash's sphere of influence. The process involves the utilization of Catia V5, SpaceClaim 22R1, MIME 8.1, CFD ++, and EXCEL software tools for tasks such as 3D modeling, geometry refinement, mesh generation, pre and post-processing, analysis, and visualization. The primary objective of this paper is to assess the induced velocity, pressure implications, and the flow-field characteristics within the proximate vicinity of the modeled helicopter rotor.