Wind Tunnel Testing of a Detonation Ramjet Model at Approach Air Stream Mach Number 5.7 and a Stagnation Temperature of 1500 K期刊界 All Journals 搜尽天下杂志传播学术成果专业期刊搜索期刊信息化学术搜索

Wind Tunnel Testing of a Detonation Ramjet Model at Approach Air Stream Mach Number 5.7 and a Stagnation Temperature of 1500 K

Authors:	S.?M.?Frolov author-information" > author-information__contact u-icon-before" > mailto:smfrol@chph.ras.ru" title=" smfrol@chph.ras.ru" itemprop=" email" data-track=" click" data-track-action=" Email author" data-track-label=" " >Email author,V.?I.?Zvegintsev,V.?S.?Ivanov,V.?S.?Aksenov,I.?O.?Shamshin,D.?A.?Vnuchkov,D.?G.?Nalivaichenko,A.?A.?Berlin,V.?M.?Fomin,A.?N.?Shiplyuk,N.?N.?Yakovlev

Affiliation:	1.Semenov Institute of Chemical Physics,Russian Academy of Sciences,Moscow,Russia;2.National Research Nuclear University MEPhI,Moscow,Russia;3.Khristianovich Institute of Theoretical and Applied Mechanics, Siberian Branch,Russian Academy of Sciences,Novosibirsk,Russia;4.PAO Turaevo Machine-Building Design Bureau “Soyuz,” Turaevo,Lytkarino,Russia

Abstract:	The mode of continuous detonation combustion of hydrogen in the annular combustor of a model of a detonation air-breathing ramjet at the approach air stream Mach number 5.7 and a stagnation temperature of 1500 K was experimentally detected for the first time in a pulsed wind tunnel. The thrust and fuelbased specific impulse of the ramjet model were 1550 N and 3300 s, respectively.

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