Wright XRJ47

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The Wright XRJ47 was an American ramjet engine developed in the 1950s to help propel the rocket-launched SM-64 Navaho supersonic intercontinental cruise missile. Although the design flight Mach Number was 2.75, a peak flight speed of Mach 3.0, at altitudes up to about 77000 ft, was envisaged. This very large ramjet had a number of design problems, including some difficulty in light-up. Development of the Navaho missile was cancelled along with the ramjet engine in 1957.

Design[]

The single cone supersonic intake supplied ram air to a long annular diffuser terminating at the aft-mounted cylindrical combustion chamber. The centreline of the intake system was gently curved, presumably to line up the intake face with the flow-field of the missile nose section.

The combustion chamber flame-holder consisted of a center-body pilot region, with three annular V-gutters interconnected by slanted radial V-gutters. Fuel jets were of variable area design.

A heat-shield, with multiple exit ports, provided cooling air for the jetpipe and the fixed area ratio convergent-divergent propelling nozzle. The exit diameter of the nozzle equaled that of the combustion chamber.

Specifications (XRJ47-W-5)[]

Data from Aircraft Engine Characteristics Summary: Ram-jet XRJ47-W-5,^[1] Preliminary evaluation of flight-weight XRJ47-W-5 ram-jet engine at a Mach number of 2.75^[2]

General characteristics

• Type: Ramjet
• Length: 390 in (9,900 mm) combustion chamber plus ducting and diffuser
• Diameter: 48 in (1,200 mm) (combustion chamber)
• Intake lip area: 636 sq in (4,100 cm²)
• Combustion chamber area: 1,810 sq in (11,700 cm²)
• Nozzle throat geometric area: 1,182 sq in (7,630 cm²)
• Nozzle exit geometric area: 1,810 sq in (11,700 cm²)
• Dry weight: 1,011 lb (459 kg)

Components

• Compressor: Ramjet inlet/diffuser
• Combustors: approx 1,887 K (2,937 °F; 1,614 °C)
• Combustion efficiency: 83.3%
• Burn time: 6500 s
• Fuel type: JP-5 (F-44 / AVCAT)

Performance

• Maximum thrust: 3,792 lbf (16.87 kN)
• Air mass flow: 59.8 lb/s (27.1 kg/s)
• Fuel consumption: 10,548 lb/h (4,784 kg/h)
• Specific fuel consumption: 2.782 lb/lbf/h (283.7 kg/kN/h)
• Thrust-to-weight ratio: 3.75

References[]

Further reading[]

• Arrighi, Robert S. (2016). Bringing the Future Within Reach: Celebrating 75 Years of the NASA. NASA.