Design Overview This aircraft design has essentially evolved to a payload compartment with wings and a tail, in the form of a conventional design. If the wing is sliced with a plane parallel to the x-z plane of the aircraft, the intersection of the wing surfaces with that plane is called an airfoil. loads are applied to the wing to check the wing reliability. •!Minimizing lift-induced drag is only one consideration in the design of wings. Span of wing box section =500mm Weight of aircraft =5000 k Factor of safety = 1.5 Design load factor = 3.2 model has been created in solid geometry. The outside geometry is given by 33 airfoils, distributed from the root to the tip of the wing, as it can be seen in figure 1 (axes in mm). 1. This airfoil shape can be In order to Therefore total design load on aircraft = 24000 kg -f Lift load on aircraft wing is 80% of total lift load on aircraft Total load acting on wings = 19200 kg -f Since we decided to carry tennis balls for Airfoils and Wings The primary lifting surface of an aircraft is its wing. Finally using an analysis software ANSYS, the design is done for the estimated takeoff weight. It is shown that the designed wing could be a good candidate for similar general aviation airplane implementation. Introduction to Aircraft Design More on lift distributions •!Few well-known aircraft ever featured an elliptical wing. Keywords: Aircraft Design, Structural Analysis . For this purpose, the development of the wings, the propeller and fuselage has been Airfoil selection..36 6.3. Wing platform design.34 6.2. Amongst all the aircraft parts reduction in the weight of the wing has got higher importance. The aerodynamic design point is at Ma=0,85 and c A=0,5. The reason for this design is twofold: Ease of construction and a result of analyzing the scoring function of the course. •!Most wings have non-elliptical lift distributions. The wing has a finite length called its wing span. For instance, 76 various wings were ... is essential to note that the wing design is a box in the iterative process of the aircraft design process. •!The lift and induced drag can be calculated for such wings using lifting line theory. 6. 9.5 Positioning of horizontal tailplanes The aim of the V-tail is to achieve a smaller tail area than with horizontal and vertical tail- planes, for example in the form of the conventional tail. 1. 9 - 7 Fig. Mechanical Engineering (Machine Design), Jntuk-University College of Engineering Vizianagaram, India _____ Abstract - This paper deals with the reduction of weight ratio in the wing structure improves the efficiency and performance of an aircraft wing. Wing Design i Chapter 5 Wing Design Mohammad Sadraey ... selections/calculations are usually repeated several times. design and development of the aircraft all tools available to the modern engineer have been properly used. Introduction . The design of an aircraft is a prolonged process that has mainly three phases; the first is includes the design calculations for the determination of airfoil, range of the wing, wing loading attributes and weight of the wing. The V-tail is designed as follows: In the first step the required areas of a conventional horizontal tailplane SH and vertical tailplane SV are determined (see below). This wing is an early design of a so-called megaliner wing, an aircraft with a wingspan of 80 meters and 400 to 500 tons maximum take off weight. Wing-in-Ground effect aircraft is one that manages level flight near the surface of the Earth, making use of the aerodynamic interaction between the wings and the surface ... 2.2.1 Manual calculation of mission weights^^^^^.13 ... Wing Design.....34 6.1. The aircraft is a two-seater model, oriented towards fast and economic travelling.