کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
1716099 | 1519998 | 2010 | 9 صفحه PDF | دانلود رایگان |
عنوان انگلیسی مقاله ISI
Thermodynamic optimization for a scramjet with Re-cooled Cycle
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کلمات کلیدی
موضوعات مرتبط
مهندسی و علوم پایه
سایر رشته های مهندسی
مهندسی هوافضا
پیش نمایش صفحه اول مقاله
![عکس صفحه اول مقاله: Thermodynamic optimization for a scramjet with Re-cooled Cycle Thermodynamic optimization for a scramjet with Re-cooled Cycle](/preview/png/1716099.png)
چکیده انگلیسی
A new Re-cooled Cycle has been proposed for a regeneratively cooled scramjet to reduce the fuel flow for cooling, fuel heat sink (cooling capacity) is repeatedly used to indirectly increase the fuel heat sink, and fuel onboard is adequate to satisfy the cooling requirement for the whole hypersonic vehicle. Parametric analysis of the Re-cooled Cycle carried out in previous study shows the potential for the cycle to be optimized. A thermodynamic optimization analysis of Re-cooled Cycle for a scramjet is obtained by satisfying hydrodynamic, thermal, and Mach number constraints. The optimal cycle parameters and length allocation between the first and second cooling passages are obtained.
ناشر
Database: Elsevier - ScienceDirect (ساینس دایرکت)
Journal: Acta Astronautica - Volume 66, Issues 9–10, May–June 2010, Pages 1449–1457
Journal: Acta Astronautica - Volume 66, Issues 9–10, May–June 2010, Pages 1449–1457
نویسندگان
Jiang Qin, Weixing Zhou, Wen Bao, Daren Yu,