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

I. O. Shamshin; D. A. Vnuchkov; D. G. Nalivaichenko; A. A. Berlin; V. M. Fomin; A. N. Shiplyuk; N. N. Yakovlev; S. M. Frolov; V. I. Zvegintsev; V. S. Ivanov; V. S. Aksenov

doi:10.1134/S0012501618070035

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

Authors: Shamshin I.O.¹^,2, Vnuchkov D.A.³, Nalivaichenko D.G.³, Berlin A.A.¹, Fomin V.M.³, Shiplyuk A.N.³, Yakovlev N.N.⁴, Frolov S.M.¹^,2, Zvegintsev V.I.³, Ivanov V.S.¹, Aksenov V.S.¹^,2
Affiliations:
1. Semenov Institute of Chemical Physics
2. National Research Nuclear University MEPhI
3. Khristianovich Institute of Theoretical and Applied Mechanics, Siberian Branch
4. PAO Turaevo Machine-Building Design Bureau “Soyuz,” Turaevo
Issue: Vol 481, No 1 (2018)
Pages: 100-103
Section: Physical Chemistry
URL: https://journals.rcsi.science/0012-5016/article/view/153879
DOI: https://doi.org/10.1134/S0012501618070035
ID: 153879

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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.