Norbert Brügge, Germany Contents: Revised: 01.06.2015 R-11 (8A61) R-11M (8K11, Scud-A) R-11MU R-11M propulsion R-17 (8K14, Scud-B) R-17M (8K14M, Scud-C) R-17 VTO R-17 propulsion Iranian Shahab-1 & -2 Iranian Qiam-1 Iraqi Al-Hussein / Al-Hijarah / Al-Abbas R-17MU (8K14MU, Scud-D) North Korean Hwasong-X Rear of a Scud-B missile without jet vanes Comparison between Scud-B and Scud-D Hwasong-5 R-17M R-17MU R-11M (Scud-A) R-17 (Scud-B) Al-Hussein-1 Al-Abbas Hwasong-6 Qiam-1 Shahab-2 (Scud-C (Scud-D Length total 10.604 m 11.164 m 10.944 m 12.264 m 13.244 m 11.166 m 11.166 m 10.500 m 12.406 m Length without control unit/ 7.441 m 7.444 m 7.444 m 8.764 m 9.740 m 7.894 m 7.894 m 7.894 m 9.134 m warhead Diameter (m) 0.88 m 0.88 m 0.88 m 0.88 m 0.88 m 0.88 m 0.88 m 0.88 m 0.88 m T-1 /AK-20F TM-185 /AK-27I TM-185 /AK-27I TM-185 /AK-27I TM-185 /AK-27I TM-185 /AK-27I TM-185 /AK-27I TM-185 /AK-27I UDMH /AK-27 Propellant Kerosene / Kerosene / Kerosene / Kerosene / Kerosene / Kerosene / Kerosene / Kerosene / Hydrazine / 80%HNO3 73%HNO3 73%HNO3 73%HNO3 73%HNO3 73%HNO3 73%HNO3 73%HNO3 73%HNO3 +27%N2O4 +20%N2O4 +27%N2O4 +27%N2O4 +27%N2O4 +27%N2O4 +27%N2O4 +27%N2O4 +27%N2O4 Mass propellant (t) 3.411 3.759 3.759 4.337 5.205 4.337 4.337 4.337 5.732 Engine S2.253 (8D511) S5.2 (9D21) S5.2 (9D21) S5.2 (9D21) S5.2 (9D21) S5.2 (9D21) S5.2 (9D21) S5.2 (9D21) Isayev Thrust s.l. (kN) 81.4 132.1 132.1 132.1 132.1 132.1 132.1 132.1 149.9 Thrust vac (kN) 94.8 146.3 146.3 146.3 146.3 146.3 146.3 146.3 165.5 Isp s.l. (Ns/kg) 2148 2285 2285 2285 2285 2285 2285 2285 2354 Isp vac Ns/kg) 2501 2530 2530 2530 2530 2530 2530 2530 2599 Burn time, nominal (sec) 90 65 65 75 90 75 75 75 90 Total vacuum impulse (MNs) 8.53 9.51 9.51 10.97 13.17 10.97 10.97 10.97 14.90 AK-27I oxidizer TM-185 fuel Concentrated Nitric Acid: 69.8 - 70.2% Polymer Distillate: 56 % (+/- 1,5 %) Di-nitrogen Tetroxide: 24 - 28% Light Oil Pyrolyse: 40 % (+/- 1 %) for the increase of the density and the resistance against the oxidation through oxygen Water: 1.3 - 2% Trikrezol: 4 % (prevents the crystallization of water) Iodium inhibitor: 0.12 -0.16% Ignition is accomplished by a hypergolic start fuel designated TG-02 "Samin" filled into the fuel line at the main fuel valve. TG-02 consists of 50 percent Tri-ethyl Amine and 50 percent Xylidiene. The propellant fed system is a turbo pump driven by a bipropellant gas generator using the main propellants. The start and shut down valves are one shot devices, actuated by pyrotechnic charges. For improving the accuracy the engine is equipped with mechanical controls for correct thrust level and mixture ratio. Tank pressurization is performed by air stored in high-pressure bottles in the missile's tail section, which are heated by the turbine exhaust gases..