نوع مقاله : گرایش پیشرانش و انتقال حرارت
نویسندگان
1 نویسنده مسئول: استادیار، دانشکده مهندسی مکانیک، دانشگاه پدافند هوایی خاتم الانبیاء(ص)، تهران، ایران
2 استادیار، دانشکده مهندسی مکانیک، دانشگاه پدافند هوایی خاتم الانبیاء(ص)، تهران، ایران
3 کارشناسی ارشد، دانشکده مهندسی مکانیک، دانشگاه پدافند هوایی خاتم الانبیاء(ص)، تهران، ایران
چکیده
تازه های تحقیق
کلیدواژه‌ها
عنوان مقاله [English]
نویسندگان [English]
Aerodynamic interference is one of the phenomena that occurs when two flying objects pass near each other. In this case, the change in the pressure distribution on objects passing near each other causes a change in the aerodynamic forces. In this research, the numerical investigation of the flow field between two narrow bodies at a close distance and the pressure changes along them at supersonic speeds is done. The simulation was done in two-dimensional and three-dimensional form, and the k-omega sst was used to model the flow turbulence. The two slender bodies were placed next to each other at speeds of Mach 1.5, 3, and 4.5 and at intervals of 2, 3, and 4 times the diameter of the body. they were examined in two modes with relative motion and without relative motion. The results show that as the free flow velocity increases, the shock wave deforms from bow to oblique and is reflected between the two bodies. Also, as the flow Mach number decreases and the distance between two slender bodies increases, the reflected shock wave becomes weaker. At Mach 1.5 the shock wave reflection between two bodies is not very noticeable, while at Mach 4.5 the shock wave is well reflected between two bodies. In the state of relative motion of two slender bodies, separation occurs at the shock wave reflection points and the number of shock wave reflections decreases compared to the state without relative movement.
کلیدواژه‌ها [English]
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