TAILIEUCHUNG - Aeronautics and Astronautics Part 2

Tham khảo tài liệu 'aeronautics and astronautics part 2', kỹ thuật - công nghệ, cơ khí - chế tạo máy phục vụ nhu cầu học tập, nghiên cứu và làm việc hiệu quả | Plasma Flow Control 29 Fig. 10. Electrical characteristics of arc discharge 3. Subsonic plasma flow control Surface dielectric barrier discharge was proved effective in subsonic plasma flow control. A great number of papers devoted to subsonic plasma flow control have appeared in the past ten years. The use of dielectric barrier discharge for flow control has been demonstrated in many applications. Examples include boundary layer acceleration transition delay lift augmentation on wings separation control for low-pressure turbine blades jet mixing enhancement plasma flaps and slats leading-edge separation control on wing sections phased plasma arrays for unsteady flow control and control of the dynamic stall vortex on oscillating airfoils. Airfoil flow separation control More than 70 lift force of aircraft is produced by wings. The lift-to-drag ratio and stall characteristic of the wing is of vital importance to the takeoff distance and climbing speed and the flight quality of the aircrafts. In order to enhance the manoeuvrability and flexibility of the aircrafts large angle of attack is used frequently. New technology should be employed into the development of aircrafts of the next generation. Active flow control technologies are considered to be the most promising technology in the 21th century. Flow separation control using microsecond and nanosecond discharge Flow separation control by microsecond and nanosecond discharge plasma aerodynamic actuation was presented. The control effects influenced by various actuation parameters were investigated. 30 Aeronautics and Astronautics The airfoil used was a NACA 0015. This shape was chosen because it exhibits well-known and documented steady characteristics as well as leading-edge separation at large angles of attack. The airfoil had a 12 cm chord and a 20 cm span. The airfoil was made of Plexiglas. Twelve pressure ports were used to obtain the pressure distribution along the model surface. Fig. 11 shows .

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