| Article ID | Journal | Published Year | Pages | File Type |
|---|---|---|---|---|
| 1717762 | Aerospace Science and Technology | 2015 | 6 Pages |
The aircraft is the second fastest means of transport. One of the most important necessities of an aircraft is the air flow over the wings to produce lift. Wing is a structure attached to the fuselage of the aircraft. Lift is an aerodynamic force which is counteracted by drag. In air transport, the cost of operation per each person/unit is higher than in the other transport because of lower passenger/load carrying capacity. One of the best ways to reduce the cost among such factors is increasing the capacity of the airplane. And this can be increased by weight carrying or lifting capacity of the airplane. Lift is controlled by the free stream flow over the wing body (main lifting body) and speed of the flow that produce drag. Most aircraft are monoplanes having one-wing structure for providing lift. Biplanes (two wings) or triplanes (three wings) were popular in the past. Due to inefficiency of the biplane and triplane (used in past days), monoplanes are in present use. To increase the efficiency of the monoplane configuration, ‘C-wing’ configuration is presented in this article. The aim is to prove, at all angles of attack, the C-wing will produce higher (L/D) ratio than straight wing for the same wetted surface area. The work undertaken here is to study the aerodynamic performance of a non-planar C-wing. This project concentrates on comparison between straight wing and C-wing with regard to characteristics like drag, stall.
