کد مقاله کد نشریه سال انتشار مقاله انگلیسی نسخه تمام متن
303736 512753 2011 8 صفحه PDF دانلود رایگان
عنوان انگلیسی مقاله ISI
Performance study of a supersonic inlet in the presence of a heat source
موضوعات مرتبط
مهندسی و علوم پایه سایر رشته های مهندسی مهندسی عمران و سازه
پیش نمایش صفحه اول مقاله
Performance study of a supersonic inlet in the presence of a heat source
چکیده انگلیسی

The flow over a supersonic inlet has been investigated experimentally and numerically at a free stream Mach number of 2 and a zero degree angle of attack. Wind tunnel tests were performed to obtain the performance parameters of the inlet and were used as a baseline and validation tools for the numerical code. A heat source was added to the flow field at a distance ahead of the inlet. The effect of heat source addition on the main performance parameters of the inlet is investigated numerically. Results show that the heat source considerably reduces drag coefficient; however, its effect on pressure recovery is not favorable. This unfavorable effect was then minimized by controlling heat source parameters, such as its location, size and shape. For the optimum condition, drag coefficient reduces considerably, inlet mass flow rate increases, but pressure recovery slightly decreases.

ناشر
Database: Elsevier - ScienceDirect (ساینس دایرکت)
Journal: Scientia Iranica - Volume 18, Issue 3, June 2011, Pages 375–382
نویسندگان
, , ,