The Lockheed X-17 was a three-stage solid-fuel research rocket to test the effects of high mach atmospheric reentry. The first stage of the X-17 carried the rocket to a height of 17 miles (27 km) before burning out.

The Lockheed X-17 was a three-stage solid-fuel research rocket to test the effects of high mach atmospheric reentry. The first stage of the X-17 carried the rocket to a height of 17 miles (27 km) before burning out.

On May 8, 1955 the first of three 1/4-scale versions of the X-17 was delivered to Cape Canaveral for flight testing. These 1/4-scale vehicles were used to test flight support hardware as well as anticipate aerodynamic performance of the proposed full-scale version of the X-17.

Sep 5, 2016 · American test vehicle. USAF X-17 flight test program at Cape Canaveral studied reentry problems by simulating reentry velocities and conditions with a three-stage solid-fuel Lockheed X-17. A total of 26 X-17 flights were conducted until March 1957.

To fulfill the need for a dedicated research vehicle, Lockheed received a contract for the design and construction of the X-17 missile in January 1955. The X-17 was a multistage vehicle using available and proven rocket motors and a relatively simple control system.

Jul 7, 2011 · The US Air Force / Lockheed X-17 was a three-stage solid-fuel rocket used to test re-entry payloads on missiles. Among the numerous technologies it tested were ablative materials for re-entry...

The Lockheed X-17 was a three stage solid-fuel research rocket to test the effects of high mach atmospheric reentry. The first stage of the X-17 carried the rocket to a height of 17 miles (27 km) before burning out.

Feb 25, 2013 · A 1958 Air Force film that documents an obscure but very important missile that was used to test the effects of hypersonic flight on early reentry vehicles. The film is introduced by Major...

The Lockheed X-17 was a three stage rocket designed to gather information about what was necessary for successful reentry to the earth’s atmosphere from outer space. The test program was successfully carried out in the mid 1950s.

Abstract : The X-17 R-26 vehicle re-entered the atmosphere at a nominal velocity of 5000 ft/sec. Second- and third-stage thrust increased the velocity to a peak value of 13,300 ft/sec. As the vehicle descended from 90,000 to 46,000 ft., the Reynolds number based on free-stream conditions and body diameter, ranged from 1.0 to 16.5 million.