Engine Model: RD-224. Manufacturer Name: RD-224. Government Designation: 8D721. Designer: Glushko. Developed in: 1960-62. Application: R-26 stage 1. Propellants: Nitric acid/UDMH. Thrust(vac): 1,778.000 kN (399,710 lbf). Isp: 294 sec. Isp (sea level): 251 sec. Burn time: 100 sec. Mass Engine: 1,250 kg (2,750 lb). Diameter: 2.27 m (7.44 ft). Length: 2.00 m (6.50 ft). Chambers: 4. Chamber Pressure: 83.40 bar. Area Ratio: 21.00. Oxidizer to Fuel Ratio: 2.50. Thrust to Weight Ratio: 145.04. Country: Russia. Status: Out of production. First Flight: 1961. RD-224 is a block of 2 RD-225s. An upper stage thrust chamber was developed under designation U102-000.
RD-224 used on Rocket Stages
Bibliography:- Glushko, V P, Albom Konstruktsiy ZhRD, Vol. 1 1968, Vol. 3 & 4 1969 via Dietrich Haeseler.