سال انتشار: ۱۳۸۶

محل انتشار: هفتمین همایش انجمن هوافضای ایران

تعداد صفحات: ۴

نویسنده(ها):

Mahmoud Passandideh-Fard – Asssistancd professor
Mehran Mohammadi Farhangi – Graduated student
Amir Omidvar – Graduated student

چکیده:

In this paper Numerical simulations are performed using the control volume method to obtain separation point of two-dimensional laminar, steady, incompressible flows. Low Reynolds number flows over cylinder, NACA 0012 and NACA 633-418 airfoil are considered under the influence of an external adverse pressure gradient for different attack angles in order to examine the accuracy of the experimental Stradford’s criteria. Then the Stradford’s criterion is amended accurately. Numerical results compared well with those of the Stratford’s criteria for NACA 633-418, NACA 0012 airfoil and cylinder.