Rocket Engines, Liquid Fuel, Dual XLR-11 (X-15 Interim Engine Pair)

Rocket Engines, Liquid Fuel, Dual XLR-11 (X-15 Interim Engine Pair)

     

This is the so-called Interim Engine of the X-15 rocket research aircraft and is made up of two joined XLR-11 rocket engines. The XLR-11 was the standard engine for the earlier Bell X-1 and other rocket research aircraft. The Interim powerplant was used in the X-15 from 1959-1961 due to developmental delays of that aircraft's newer and more powerful XLR-99 Pioneer rocket engine. The Interim engines achieved the X-15's first 29 powered flights. The Interim engine produced a total of 16,400 pounds from its four chambers and was sufficient for the preliminary test flights of the X-15. It achieved some notable records in that phase of the X-15 program. This Interim Engine was transferred to the Smithsonian in 1963 from the U.S. Air Force.

Transferred from the U.S. Air Force

Country of Origin
United States of America

Manufacturer
Reaction Motors, Inc.

Date
ca. 1959-1961

Type
PROPULSION-Rocket Engines

Materials
Mainly stainless steel, some titanium, some copper alloy tubing; pump housing, cast aluminum; insulated electrical wiring.
Dimensions
Length, 82 inches; width, 42 inches; height, 48 inches; length, thrust cylinders (8), 21.75 inches each; diameter, cylinders (8), 6 inches each; weight, approximately 500 pounds (empty weight of each XLR-11 is 210 pounds).

This is the so-called Interim Engine of the X-15 rocket research aircraft and is made up of two joined XLR-11 rocket engines. The XLR-11 was the standard engine for the earlier Bell X-1 and other rocket research aircraft. The Interim powerplant was used in the X-15 from 1959-1961 due to developmental delays of that aircraft's newer and more powerful XLR-99 Pioneer rocket engine. The Interim engines achieved the X-15's first 29 powered flights. The Interim engine produced a total of 16,400 pounds from its four chambers and was sufficient for the preliminary test flights of the X-15. It achieved some notable records in that phase of the X-15 program. This Interim Engine was transferred to the Smithsonian in 1963 from the U.S. Air Force.

Transferred from the U.S. Air Force

Country of Origin
United States of America

Manufacturer
Reaction Motors, Inc.

Date
ca. 1959-1961

Type
PROPULSION-Rocket Engines

Materials
Mainly stainless steel, some titanium, some copper alloy tubing; pump housing, cast aluminum; insulated electrical wiring.
Dimensions
Length, 82 inches; width, 42 inches; height, 48 inches; length, thrust cylinders (8), 21.75 inches each; diameter, cylinders (8), 6 inches each; weight, approximately 500 pounds (empty weight of each XLR-11 is 210 pounds).

ID: A19630364000