عنوان
پدید آورنده
موضوع
رده
کتابخانه
محل استقرار
TLpq304574634
انگلیسی
Wind tunnel testing of an airfoil with a moving surface boundary-layer control
[Thesis]
A. M. Al-Garni
King Fahd University of Petroleum and Minerals (Saudi Arabia)
1999
116
M.S.
King Fahd University of Petroleum and Minerals (Saudi Arabia)
1999
The control of boundary layer is very important in the field of aerodynamics and hydrodynamics and becomes essential for current wing design technology to increase lift, stalling angle of attack and lift-to-drag ratio. Therefore, an experimental investigation has been conducted on a two-dimensional airfoil, NACA 0024, equipped with a moving surface to control the boundary layer. The moving surface, which is the surface of a rotating cylinder, is located at the leading edge of the airfoil. The airfoil was tested for different values of usdU\sb{c}/Uusd and usd\deltausd. This investigation includes the effects of usd\alpha,\ U\sb{c}/Uusd, and usd\deltausd on lift and drag coefficients, the size of the separated flow region and the stalling angle of attack. In addition to these, the study shows the effect of usdU\sb{c}/Uusd on the boundary layer growth and turbulence intensity. Experimental results showed that the leading-edge rotating cylinder increases the lift coefficient of the NACA 0024 airfoil from 0.85 for usdU\sb{c}/Uusd = 0 to 1.63 for usdU\sb{c}/Uusd = 4 and delays the stalling angle of attack by about 160%. The smoke-wire flow visualization results were used to demonstrate the tremendous effect of the leading-edge rotating cylinder on the size of the recirculation region.
Aerospace materials
Applied sciences
Mechanical engineering
A. M. Al-Garni
مطالعه متن کتاب p
[Thesis]
276903
a
Y
