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Aircraft Wings Advantages And Disadvantages

811 Words4 Pages

The aircraft wings are the primary lift producing device for an aircraft. The aircraft wings are designed aerodynamically to generate a lift force which is required in order for an aircraft to fly. Besides generating the necessary lift force, the aircraft wings are used to carry the fuel required for the mission of the aircraft, can have mounted engines or can carry extra fuel tanks or other armaments. The basic goal of the wing is to generate lift and minimize drag as far as possible. When the airflow passes the wing at any suitable angle of attack, a pressure differential is created. A region of lower pressure is created over the top surface of the wing while, a region of higher pressure is created under the surface of the wing. This difference …show more content…

Also, the aircraft wings have to deal with aero-elastic and structural loads as well. Therefore, the aircraft wings must be designed structurally and aerodynamically well for providing good overall performance in all phases of flight. The weight of the wing is a considerable parameter while considering the overall performance. Weight reduction of aircraft wing will increase the flight performance. Use of isotropic material will add more weight while comparing to the composite material. Composite materials are materials made from two or more constituent materials with significantly different physical or chemical properties, that when combined, produce a material with characteristics different from the individual components. The individual components remain separate and distinct within the finished …show more content…

Modern aircraft structures are designed using a semi-monocoque concept. A basic load-carrying shell reinforced by skin construction supported by spars and ribs in the surfaces. Modern finite element models of aircraft components include tens-of-thousands of degrees-of-freedom and are used to determine the required skin thicknesses to avoid excessive stress levels, deflections, strains, or buckling. The goals of detailed design are to reduce or eliminate stress concentrations, and decreasing the deflection of wing with increasing the structure or placements of structural members. Fail-safe design is achieved through material selection, proper stress levels, and load path, structural arrangements which maintain high strength in the presence of deflection. Stress levels are adjusted to achieve required structural

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