Lake Renegade

Renegade, Seafury, Seawolf
Seawolf operated by NOAA
Role Utility amphibian
National origin United States
Manufacturer Lake Aircraft
First flight 1982
Developed from Lake Buccaneer
LA-270 Turbo Renegade
LA-4-250 Seawolf

The Lake LA-250 Renegade is a six-seat amphibious utility aircraft produced in the United States by Lake Aircraft since 1982.[1]

Design and development

The Renegade is a lengthened and more powerful version of the Lake Buccaneer. They share the Buccaneer's type certificate, and Buccaneer production was terminated.[2] In turn, it gave rise to a number of variants, including the militarised LA-250 Seawolf, the turbocharged LA-270 Turbo Renegade, and the LA-270 Seafury optimised for marine environments.[1][2] Like the Buccaneer, it is a conventional mid-wing design with retractable tricycle undercarriage and a single engine mounted in pusher configuration in a pod on a pylon above the fuselage.[3]

The Seawolf version was designed for light maritime patrol duties and features a hardpoint under each wing to carry external stores, including bombs, rocket pods, gun pods, or rescue equipment.[3] Provision for a radar unit was made on the forward end of the engine pod.[3][4] The Seafury includes improved anti-corrosion measures and a hardened interior to improve its serviceability in saltwater environments, as well as a storage compartment carrying survival gear.[5]

Operational history

In 1988 Peter Foster and Robert Mann piloted a Turbo Lake Renagade to an altitude of 24,500 feet, setting a new world record for altitude and sustained flight at altitude for single-engine seaplanes.[6]

Variants

  • LA-250 Renegade — Buccaneer with 38-inch (97-cm) fuselage stretch, six seats, and Lycoming IO-540-C4B5 engine
    • LA-250 Seawolf — militarised Renegade with hardpoints and provision for radar
  • LA-270 Turbo Renegade — Renegade with Lycoming TIO-540-AA1AD engine uprated to 270 hp (200 kW)
    • LA-270 Seafury — Renegade for saltwater conditions

Specifications (LA-250)

Data from Jane's All the World's Aircraft 1984–85, 431 and The Incomplete Guide to Airfoil Usage[7]

General characteristics

  • Crew: one pilot
  • Capacity: five passengers
  • Length: 28 ft 4 in (8.64 m)
  • Wingspan: 38 ft 0 in (11.58 m)
  • Height: 10 ft 0 in (3.05 m)
  • Wing area: 170 ft2 (15.8 m2)
  • Wing profile: NACA 4418 (root), NACA 4412 (tip)
  • Empty weight: 1,850 lb (839 kg)
  • Gross weight: 3,050 lb (1,383 kg)
  • Powerplant: 1 × Lycoming IO-540-C4B5, 250 hp (186 kW)

Performance

  • Maximum speed: 160 mph (258 km/h)
  • Range: 1,036 miles (1,668 km)
  • Service ceiling: 14,700 ft (4,480 m)
  • Rate of climb: 900 ft/min (4.6 m/s)

Notes

  1. 1 2 Taylor 1989, 932
  2. 1 2 Simpson 1995, 226
  3. 1 2 3 Jane's All the World's Aircraft 1985–85, 432
  4. ↑ Simpson 1995, 227
  5. ↑ Simpson 1995, 228
  6. ↑ Air Progress: 21. February 1989. Missing or empty |title= (help)
  7. ↑ Lednicer, David (2010). "The Incomplete Guide to Airfoil Usage". Retrieved 11 September 2013.

References

  • Jane's All the World's Aircraft 1984–85. London: Jane's Publishing.
  • Simpson, R. W. (1995). Airlife's General Aviation. Shrewsbury: Airlife Publishing.
  • Taylor, Michael J. H. (1989). Jane's Encyclopedia of Aviation. London: Studio Editions.

Official website

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