کد مقاله | کد نشریه | سال انتشار | مقاله انگلیسی | نسخه تمام متن |
---|---|---|---|---|
5145643 | 1497337 | 2017 | 13 صفحه PDF | دانلود رایگان |
عنوان انگلیسی مقاله ISI
Wind tunnel tests of a hydrogen-fueled detonation ramjet model at approach air stream Mach numbers from 4 to 8
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کلمات کلیدی
موضوعات مرتبط
مهندسی و علوم پایه
شیمی
الکتروشیمی
پیش نمایش صفحه اول مقاله
چکیده انگلیسی
Experimental studies of an axisymmetric hydrogen-fueled detonation ramjet model 1.05-m long and 0.31Â m in diameter with an expanding annular combustor were performed in a pulse wind tunnel under conditions of approaching air stream Mach number ranging from 4 to 8 with the total temperature of 290Â K. In a supersonic air flow entering the combustor, continuous and longitudinally pulsating modes of hydrogen detonation with the corresponding characteristic frequencies of 1250 and 900Â Hz were obtained. The maximum measured values of fuel-based specific impulse and total thrust were 3600Â s and 2200Â N.
ناشر
Database: Elsevier - ScienceDirect (ساینس دایرکت)
Journal: International Journal of Hydrogen Energy - Volume 42, Issue 40, 5 October 2017, Pages 25401-25413
Journal: International Journal of Hydrogen Energy - Volume 42, Issue 40, 5 October 2017, Pages 25401-25413
نویسندگان
S.M. Frolov, V.I. Zvegintsev, V.S. Ivanov, V.S. Aksenov, I.O. Shamshin, D.A. Vnuchkov, D.G. Nalivaichenko, A.A. Berlin, V.M. Fomin,