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- Engine, Fredric Flader XJ55-FF-1 Turbojet
Engine, Fredric Flader XJ55-FF-1 Turbojet
Object Details
- Physical Description
- Type: Turbojet
- Thrust: 3,425 N (770 lb)
- Compressor: Single-stage axial supersonic
- Combustor: Annular
- Turbine: Single-stage axial
- Weight: 136 kg (300 lb)
- Summary
- In 1948, the Army Air Forces awarded a contract to Ryan to develop the XQ-2 jet-powered target aircraft. To power the aircraft, the Wright Air Development Center had earlier awarded a contract to Fredric Flader, Inc. for the XJ55-FF-1 turbojet engine, with a unique feature being its single-stage "shock-in-rotor" (supersonic) axial-flow compressor.
- At the beginning of 1952, a Flader development engine obtained the contractually specified thrust of 3,136 N (700 lb). Unfortunately, it was necessary to exceed the specified turbine design turbine to achieve that thrust and, after one minute, the turbine failed and the engine blew up. As a result, the Air Force recommended that work on the XJ55 be terminated due to its technical shortcomings, and because the Fairchild YJ44 and French Turbomeca Marbore II (later J69), licensed to Continental, were suitable substitute engines for the XQ-2. This cancellation ended Flader's aircraft gas turbine engine development.
- Credit Line
- Transferred from the U.S. Air Force Museum, Wright-Patterson AFB, Ohio
- Data Source
- National Air and Space Museum
- Date
- Circa 1948
- Inventory Number
- A19600244000
- Manufacturer
- Fredric Flader (Tonawanda, New York)
- Restrictions & Rights
- Usage conditions apply
- Type
- PROPULSION-Turbines (Jet)
- Materials
- HAZMAT: Cadmium Plating, Magnesium Alloy
- Steel
- Aluminum
- Anodized Aluminum
- Copper Alloy
- Stainless Steel
- Rubber
- Wood
- Plastic
- Adhesive
- Paint
- Paper
- Natural Fabric
- Ceramic
- Dimensions
- Length 181.6 cm (71.5 in.), Diameter 38.9 cm (15.3 in.)
- Country of Origin
- United States of America
- See more items in
- National Air and Space Museum Collection
- Record ID
- nasm_A19600244000
- Usage
- Not determined