Original Soviet missile designator R-17, system designator 8K14 or 9K72; NATO designator Scud B; DIA (Defense Intelligence Agency) designator SS-1B.

Missile type: Liquid propellant, single-stage, mobile, ballistic missile

Analysis note: All data are nominal figures from the Soviet missile handbook (some small deviations exist in the original documents)

Missile Data	Unit	Value/Description
Overall mass\t	Kg	5860 - 5862
Thrust	kN	130.52
Sea level spec. Impulse	S	230.2
Length\t	M	10.944
Diameter	M	0.88
Wing Span	M	1.8
HE warhead mass	Kg	987 - 989
Dry net mass\t	Kg	2076
Dry inert mass\t	Kg	1087 - 1089
Propellant mass	Kg	3771
Gas (for tank pressurization)	Kg	15
Propellant load	S	65.2
Total propellant flow	kg/s	57.83
Propellant consumption ratio (ox/fuel)		3.52
Combustion chamber pressure	bar	69
Expansion ratio throat/nozzle		8
Residual propellant at cut off	kg	156
Maximum nominal range	Km	300
Maximum guaranteed range	Km	275 under worst conditions (handbook)
Minimum range	Km	50
Nominal burning time\t	S	61.95 design point
Guaranteed life span of 9D21 engine		>100 s
Engine type		Single chamber liquid rocket motor with a gas generator driven by single shaft turbo pump
Propellants\t		AK 27I, TM 185; ignition by 35 liters TG-02 start fuel
Airframe		Separate propellant tanks made of stainless steel with internal double-walled fuel line
Guidance		three body-mounted gyros: two for attitude sensing and one for lateral acceleration plus one PIGA
Pitch (program)		3 s @ 90°, 12 s @ 70°, 48 s @ 45.5°
Velocity at cut off		14592 m/s at 28 km altitude
Reentry velocity at 16 km altitude		1588 m/s
Terminal velocity (ground level):		1154 m/s
CEP		Uncertain. Probably 800 m at max range. Better at 2/3 range

	Updated April 2003