Design and Simulation of Numerical Model for Fixed Wing Aircraft Hybridized with Tricopter

Abstract

The traditional Fixed Wing aircraft requires a long runway. It is incapable of a vertical take-off and landing (VTOL) scenario. Also its maneuvering capability around objects is limited. This makes it inaccessible for certain applications. On the other hand the Rotary Wing Aircraft (Quadcopter or Helicopter) will have the VTOL ability. But the disadvantage is its slow operational speed. Also the consumption of energy is greater than a Fixed Wing aircraft. To solve these issues, the proposed aircraft is fixed Wing Aircraft Hybridized with Tri-copter. It has higher efficiency and can attain higher speeds than a Tri-copter or Helicopter. This Thesis discusses how to Design and analysis of VTOL aircraft. The wing of the Aircraft has been successfully analyzed using Ansys-15 software to answer some aerodynamic questions associated with the wing. The lift and drag coefficients are calculated over a range of angles of attack (0°-20°). The results lend into the choice of best angles of attack (5°) and the range at which the aircraft must fly (5°-15°).