سال انتشار: ۱۳۸۶

محل انتشار: پانزدهمین کنفرانس سالانه مهندسی مکانیک

تعداد صفحات: ۶

نویسنده(ها):

Akbarzadeh – Graduate Student Department of Mechanical Engineering Amirkabir University of Technology (Tehran Polytechnic)
Kermani – Assistant Professor Department of Mechanical Engineering Amirkabir University of Technology (Tehran Polytechnic)

چکیده:

The performance of three different ramjet engine inlets is numerically considered in this study. The geometries used are planar with the free stream Mach = 2.5. Inlet 1 is chosen from literature, a single oblique shock followed by a normal one, which given a low value of total pressure recovery. Inlets 2 and 3 are designed in a way to produce a series of oblique shocks merging at the cowl lip of the engine followed by a normalhock. The compression process in inlet 2 is completely performed in external part of the inlet. Instead inlet 3 is given a mixed internal and external compression. Inviscid Roe scheme with 3rd order accurate in space and second order accurate in time and second order predictor-corrector MacCormack scheme are applied in this study and also commercial FLUENT software package. The results are in good agreementwith literature.