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Lockheed X-17

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colspan="2" Template:WPMILHIST Infobox style | Lockheed X-17
colspan="2" Template:WPMILHIST Infobox style | 300px
Type Atmospheric reentry testing
colspan="2" Template:WPMILHIST Infobox style | Production history
Manufacturer Lockheed
colspan="2" Template:WPMILHIST Infobox style | Specifications
Length 40 ft 4 in (12.3 m)
Diameter 1st stage: 2 ft 7 in (0.79 m)
2nd stage: 2 ft 5 in (0.43 m)
3rd stage: 0 ft 9.7 in (0.25 m)

Engine 1st stage:1x Thiokol XM20 Sergeant solid-fuel rocket, 48,000 lbf (213 kN)
2nd stage:3x Thiokol XM19 Recruit solid-fuel rocket, 33,900 lbf (150 kN) (each)
3rd stage:1x Thiokol XM19E1 Recruit solid-fuel rocket, 35,950 lbf (160 kN)
Wingspan 7 ft 7 in (2.3 m)
135 miles (217 km)
Flight altitude 250 mi (400 km)
Speed Mach 14.5
File:Lockheed X-17 launchplatform.jpg
Lockheed X-17 on its launching platform

The Lockheed X-17 was a three stage solid-fuel research rocket to test the effects of high mach reentry. The first stage of the X-17 carried the rocket to a height of Template:Convert before burning out. The rocket would then coast on momentum to about Template:Convert before nosing down for reentry. The second stage engine would then fire before jettisoning and igniting the third and final stage. On April 24, 1957, an X-17 reached a speed of Template:Convert at Patrick AFB.[1] Ultimately the X-17 would be travelling towards earth at up to Mach 14.5.

The X-17 was also used as the booster for the Operation Argus series of three high-altitude nuclear tests conducted in the South Atlantic in 1958.[2]


  1. E. Emme, ed., Aeronautics and Astronautics, 1915-1960, p. 85.
  2. Carey Sublette (20 September 1997). Operation Argus tests. Nuclear Weapon Archive. Retrieved on 2008-01-11.


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This article is licensed under the GNU Free Documentation License.
It uses material from the Wikipedia article "Lockheed X-17".