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A Study on the Reduction of Drag and Heat Transfer on a Conventional Hypersonic Nose Cone | ||
| Journal of Heat and Mass Transfer Research | ||
| دوره 12، شماره 2 - شماره پیاپی 24، بهمن 2025، صفحه 393-411 اصل مقاله (3.21 M) | ||
| نوع مقاله: Full Length Research Article | ||
| شناسه دیجیتال (DOI): 10.22075/jhmtr.2025.36388.1667 | ||
| نویسندگان | ||
| Mohammad Hadi Islamy* 1؛ Mohsen Sargolzayi1؛ Esmaeil Yaddollahi Afra2 | ||
| 1Qadr Aerodynamic Institute, Imam Hossein University, Tehran, 1698715461, Iran | ||
| 2Department Aerospace Engineering, Faculty of New Sciences and Technologies, Semnan University, Semnan, 19111-35131, Iran | ||
| تاریخ دریافت: 11 دی 1403، تاریخ بازنگری: 18 بهمن 1403، تاریخ پذیرش: 26 اسفند 1403 | ||
| چکیده | ||
| In the present study, the effect of jet injection on two geometries—single-cone and double-cone—subjected to hypersonic flow is investigated. The simulations are performed using ANSYS-Fluent software. The baseline case is one where the nose lacks injection. The single-cone nose is tested at Mach 6, and the double-cone nose at Mach 5.4. The results show that increasing injection pressure results in a drag coefficient reduction of 49.2% for the single-cone geometry and 62.7% for the double-cone geometry, compared to the baseline. Additionally, the heat flux decreases by 60% for the single-cone nose and 41.3% for the double-cone nose. Higher injection pressure leads to an increase in bow shock standoff distance upstream of both the single-cone and double-cone noses. Increasing injection temperature has minimal impact on the drag coefficient and pressure distribution on the surface of the single-cone nose but significantly reduces the Stanton number, thereby decreasing heat transfer and enhancing nose cooling. Increasing the injection diameter from zero to 5 mm in the single-cone nose results in a 23% reduction in drag coefficient, while for the double-cone geometry, increasing the diameter to 16.5 mm reduces the drag coefficient by 75.04%. Changing the fluid type from air to a gas mixture decreases the maximum Stanton number by 19.3%. | ||
| کلیدواژهها | ||
| Single-Cone Nose؛ Double-Cone Nose؛ Stanton Number؛ Pressure Distribution؛ Drag Coefficient | ||
| عنوان مقاله [English] | ||
| مطالعهای بر کاهش نیروی پسا و انتقال حرارت در یک دماغه ماوراءصوت متداول | ||
| چکیده [English] | ||
| در مطالعه حاضر، تأثیر تزریق جت بر دو هندسه—مخروط تک و مخروط دوگانه—تحت جریان ماوراءصوت بررسی شده است. شبیهسازیها با استفاده از نرمافزار ANSYS-Fluent انجام شدهاند. حالت پایه، حالتی است که در آن هیچ تزریقی در دماغه صورت نمیگیرد. دماغه مخروط تک در ماخ 6 و دماغه مخروط دوگانه در ماخ 5.4 آزمایش شدهاند. نتایج نشان میدهد که افزایش فشار تزریق منجر به کاهش ضریب پسا به میزان 49.2% برای هندسه مخروط تک و 62.7% برای هندسه مخروط دوگانه در مقایسه با حالت پایه میشود. علاوه بر این، شار حرارتی به میزان 60% برای دماغه مخروط تک و 41.3% برای دماغه مخروط دوگانه کاهش مییابد. فشار تزریق بالاتر باعث افزایش فاصله ایستگاه شوک قوس در بالادست هر دو دماغه مخروط تک و مخروط دوگانه میشود. افزایش دمای تزریق تأثیر کمی بر ضریب پسا و توزیع فشار روی سطح دماغه مخروط تک دارد اما عدد استانتون را به طور قابل توجهی کاهش میدهد و در نتیجه انتقال حرارت کاهش یافته و خنکسازی دماغه بهبود مییابد. افزایش قطر تزریق از صفر تا 5 میلیمتر در دماغه مخروط تک منجر به کاهش 23% در ضریب پسا میشود، در حالی که برای هندسه مخروط دوگانه، افزایش قطر تا 16.5 میلیمتر ضریب پسا را به میزان 75.04% کاهش میدهد. تغییر نوع سیال از هوا به مخلوط گازی، عدد استانتون حداکثر را به میزان 19.3% کاهش میدهد. | ||
| کلیدواژهها [English] | ||
| دماغه مخروط تک, دماغه مخروط دوگانه, عدد استانتون, توزیع فشار, ضریب پسا | ||
| مراجع | ||
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