Analysis of a Highly Manoeuvre Penta rotor Aircraft using CFD Shikha Gupta 1 Soorya Kumar 1 Yadvender Singh Dhillon 1 A.J.Arun Jeya Prakash 2 Karthik Sundarraj 2 1 B.tech Final Year Students, 2 Asst Professor 1,2 Department of Aerospace Engineering, University of Petroleum and Energy Studies, Dehradun, Uttarakhand ,India 248007. 1 shikha.gupta248@gmail.com, 1 soorya.avionics@gmail.com, 1 ydhillon7@gmail.com, 2 ajp.mit@gmail.com, ABSTRACT This work focuses on the Computational Fluid Dynamics (CFD) analysis of a high manoeuvre penta rotor aircraft. The aircraft design calculations were done manually and modelling is done in solid works. The concept for designed UAV is that it can take off and land vertically and can be accelerated in forward flight regime using a rotor in pusher configuration. The penta rotor aircraft design with and without winglet configuration and its aerodynamic properties were analyzed using CFD for validation of the designs. The CFD analysis of the different models has been successfully completed in CFD for the forward flight regime. The airfoil used for the UAV is NACA4412. The coefficient of Lift and Drag and Pitching Moment are plotted against various angles of attack and the results obtained are satisfactory for the designs. Introduction: Penta rotor Aircrafts are an emerging rotorcraft concept for Unmanned Aerial Vehicle (UAV) platforms. The vehicle consists of five rotors in total. Due to its specific capabilities, use of autonomous quad rotor vehicles has been envisaged for a variety of applications both as individual vehicles and in multiple vehicle teams, including surveillance, search and rescue and mobile sensor networks. The particular interest of the research community in the quad rotor design can be linked to two main advantages over comparable vertical take-off and landing (VTOL) UAVs. First, penta rotors do not require complex mechanical control linkages for rotor actuation, relying instead on fixed pitch rotors and using variation in motor speed for vehicle control. This simplifies both the design and maintenance of the vehicle. Second, the use of five rotors ensures that individual rotors are smaller in diameter than the equivalent main rotor on a helicopter, relative to the airframe size. The individual rotors, therefore, store less kinetic energy during flight; mitigating the risk posed by the rotors should they entrain any objects. Furthermore, by enclosing the rotors within a frame, the rotors can be protected from breaking during collisions, permitting flights indoors and in obstacle-dense environments, with low risk of damaging the vehicle, its operators, or its surroundings. These added safety benefits greatly accelerate the design and test flight process by allowing testing to take place indoors, by inexperienced pilots, with a short turnaround time for recovery from incidents. 15th Annual CFD Symposium, August 9-10, 2013, Bangalore, India 1 Contents