International Journal of Advancements in Mechanical and Aeronautical Engineering – IJAMAE Copyright © Institute of Research Engineers and Doctors Volume 6 : Issue 1- [ISSN : 2372-4153] - Publication Date: 10 May, 2019 15 Design and Analysis of Flying Wing UAV using XFLR5 Sai Vinay Sandapeta, Sai Kiran Parre, Yakkaluru Dedeepya, Habeeb Jaffar al Aidroos, Mariyada Vamshi Krishna Reddy Abstract— This paper presents the design and analysis of flying wing UAV. The design and analysis was performed using XFLR5 code (an interactive program for the design and analysis of subsonic UAVs), where the Mathematical Modeling with efficient numerical method i.e. Vortex Lattice Method (VLM1) through XFLR5 results of Flying Wing UAV of the airfoil MH 60 10.08% (Martin Hepperle MH 60 for flying wings Max thickness 10.1% at 26.9% chord & Max camber 1.7% at 36.6% chord) is discussed. Keywords— flying wing UAV, Tailless aircraft, Body-less model aircraft, Aerodynamic Design Static Stability, longitudinal stability, lateral stability. Sai Vinay Sandapeta ( UG Student) Department of Aeronautical Engineering, Institute of Aeronautical Engineering, Hyderabad, India Sai Kiran Parre ( UG Student) Department of Aeronautical Engineering, Institute of Aeronautical Engineering, Hyderabad, India Yakkaluru Dedeepya ( UG Student) Department of Aeronautical Engineering Institute of Aeronautical Engineering, Hyderabad, India Habeeb Jaffar al Aidroos ( UG Student) Department of Aeronautical Engineering Institute of Aeronautical Engineering, Hyderabad, India I. Introduction The importance of UAV in operations and the unprecedented variety deployed today is growing. The UAVs can be used both for military , civilian and Commercial purposes such as science & Research (Forest and Natural Resources Management , Studying Biodiversity , Measuring nuclear contamination , climate observation , Meteorological Research ) , Security ( Anti-Terror Operations , Criminal Investigation , Traffic Surveillance , Searching for missing persons , Emergency communication networks , Anti – privacy operations , Monitoring International summit meetings) , Inspections ( Oil, Gas & Methane pipelines, Solar panel , power line / cable , cooling tower ,Bridge , Dams) , cargo delivery application, construction applications and surveying applications. These Indications are that there is a growing market for this type of aircraft. So next-generation UAVs will require low-cost and efficient configurations. Many of existing UAV use conventional (i.e.: low/mid/high-wing, fuselage tail and tractor engine) and unconventional (i.e.: flying wing, three surfaces, low/mid/high-wing, high aspect ratio wing, fuselage tail/canards/inverted V-tail and pusher engine) configurations. The design of low-cost and efficient configurations of UAV becomes increasingly more important for improving the performances, flight characteristics, handling qualities and UAV operations. Most of small UAV fly at low Reynolds number, this allow to uses fuselage-wing-tail with laminar flow technology, to improve its cruise performance. Therefore, the understanding of and ability to design and analyze those configuration and technology for UAV is a problem that must be solved in order to allow the UAV designer to develop a UAV which satisfy the prescribe design requirements and objectives. However, the presence of unconventional configuration and laminar flow technology seriously complicates design and analysis procedures because of important and often complex interaction between the individual elements of UAV often present very different and distinct challenges. Here in this paper, we have flying wing configuration where the wing is everything. It does not have a conventional tube type fuselage for payload. All structure, engine and payload are fixed inside the wing. The design and analysis of it done through VLM1 Mathematical Modeling by XFLR5. Fig 1: Flying wing designe d in XFLR5 II. Airfoil Selection and analysis Conventional cambered airfoils produce a negative pitching moment (Cm), nose-down effect, on the airfoil. This is counteracted through the empennage by the horizontal stabilizers. In a flying wing type aircraft, careful selection of the airfoils is essential, since Cm strongly contributes to the aerodynamic longitudinal stability of the aircraft