Engine Model: EKR Ramjet. Designer: Bondaryuk. Developed in: 1953-54. Application: EKR Stage 2. Propellants: Air/Kerosene. Thrust(vac): 6.130 kN (1,378 lbf). Isp: 1,580 sec. Burn time: 800 sec. Chambers: 1. Country: Russia. Status: Study 1953. Study for an experimental winged cruise missile. Not developed but formed basis for Burya and Buran missiles. Thrust is maximum thrust at cruise altitude. Specific impulse is that at cruise design point.
EKR Ramjet used on Rocket Stages
Bibliography:- Semenov, Yuri P Editor, Raketno-kosmicheskaya korporatsiya 'Energia' imeni S P Koroleva, Moscow, Russia, 1996.