Contents:

R-11 (8A61)R-11M (8K11, Scud-A)R-11MUR-11M propulsion R-17 (8K14, Scud-B)R-17M (8K14M, Scud-C)R-17 VTOR-17 propulsion

Iranian Shahab-1 & -2Iranian Qiam-1Iraqi Al-Hussein / Al-Hijarah / Al-AbbasR-17MU (8K14MU, Scud-D)North Korean Hwasong-XNorbert Brgge, Germany

Revised: 01.06.2015

Rear of a Scud-B missile without jet vanes

Comparison between Scud-B and Scud-D

R-11M (Scud-A)R-17 (Scud-B)Hwasong-5Shahab-2Al-Hussein-1Al-AbbasR-17M(Scud-CHwasong-6Qiam-1R-17MU(Scud-D

Length total10.604 m11.164 m10.944 m12.264 m13.244 m11.166 m11.166 m10.500 m12.406 m

Length without control unit/ warhead7.441 m7.444 m7.444 m8.764 m 9.740 m7.894 m7.894 m7.894 m 9.134 m

Diameter (m)0.88 m0.88 m0.88 m0.88 m0.88 m0.88 m0.88 m0.88 m0.88 m

PropellantT-1 /AK-20FTM-185 /AK-27ITM-185 /AK-27ITM-185 /AK-27ITM-185 /AK-27ITM-185 /AK-27ITM-185 /AK-27ITM-185 /AK-27IUDMH /AK-27

Kerosene /80%HNO3 +20%N2O4Kerosene /73%HNO3 +27%N2O4Kerosene /73%HNO3 +27%N2O4Kerosene /73%HNO3 +27%N2O4Kerosene /73%HNO3 +27%N2O4Kerosene /73%HNO3 +27%N2O4Kerosene /73%HNO3 +27%N2O4Kerosene /73%HNO3 +27%N2O4Hydrazine /73%HNO3 +27%N2O4

Mass propellant (t)3.4113.7593.7594.3375.205 4.3374.3374.3375.732

EngineS2.253 (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)81.4132.1132.1132.1132.1132.1132.1132.1149.9

Thrust vac (kN)94.8146.3146.3146.3146.3146.3146.3146.3165.5

Isp s.l. (Ns/kg)214822852285228522852285228522852354

Isp vac Ns/kg)250125302530253025302530253025302599

Burn time, nominal (sec)9065657590 75757590

Total vacuum impulse (MNs)8.539.519.5110.9713.17 10.9710.9710.9714.90

TM-185 fuelPolymer Distillate: 56 % (+/- 1,5 %)Light Oil Pyrolyse: 40 % (+/- 1 %) for the increase of the density and the resistance against the oxidation through oxygenTrikrezol: 4 % (prevents the crystallization of water)AK-27I oxidizer Concentrated Nitric Acid: 69.8 - 70.2% Di-nitrogen Tetroxide: 24 - 28%Water: 1.3 - 2%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.