سال انتشار: ۱۳۸۹

محل انتشار: دهمین همایش انجمن هوافضای ایران

تعداد صفحات: ۷

نویسنده(ها):

Mahmood Pasandideh fard – Associated Professor Department of Mechanical and Aerospace Engineering, Ferdowsi University of Mashhad
Maryam Moein far – M.Sc. Student,
Seyed Morteza Abdollahian – M.Sc. Student

چکیده:

In this paper flow fields over delta and arrow wings with various sweep angles and thicknesses at different angles of attack and Mach numbers from subsonic to supersonic flow are computationally simulated. There is a sudden change in flow fields between the free stream Mach number of 0.8 and 1.2. The simulation results at different flow conditions, show that this nonlinear behavior occurs as expansion waves from the leadingedge accelerate the flow and shift the share layer closer to the surface when the Mach number at the leading edge becomes supersonic. The aerodynamic characteristics have a different trend below and above the free-stream Mach number of 1.0. So when the flow regime becomes supersonic, aerodynamic characteristics have nonlinear behavior.