Bell X-1 - Design and Development

Design and Development

On 16 March 1945, the U.S. Army Air Forces Flight Test Division and the National Advisory Committee for Aeronautics (NACA) made a contract with the Bell Aircraft Company to build three XS-1 (for "Experimental, Supersonic", later X-1) aircraft to obtain flight data on conditions in the transonic speed range.

The X-1 was in principle a "bullet with wings", its shape closely resembling a Browning .50-caliber (12.7 mm) machine gun bullet, known to be stable in supersonic flight. The pattern shape was followed to the point of seating its pilot behind a sloped, framed window inside a confined cockpit in the nose, with no ejection seat. After the rocket plane ran into compressibility problems in 1947, it was modified with variable-incidence tailplane. An all-moving tail was developed by the British for the Miles M.52, but was first used in transonic flight on the X-1, allowing it to pass through the sound barrier safely.

The rocket propulsion system was a four-chamber engine built by Reaction Motors, Inc., one of the first companies to build liquid-propellant rocket engines in America. This rocket burned ethyl alcohol diluted with water with a liquid oxygen oxidizer. Its thrust could be changed in 1,500 lbf (6,700 N) increments by firing just one or more than one of its chambers. The fuel and oxygen tanks for the first two X-1 engines were pressurized with nitrogen gas, but the rest used steam-driven turbopumps. The all-important fuel turbopumps, necessary to raise the chamber pressure and thrust while making the engine lighter, were built by Robert Goddard, who was under a contract with the U.S. Navy to provide jet-assisted takeoff (JATO) rockets.