Uetz Pelikan

From Wikipedia, the free encyclopedia
  (Redirected from Uetz U4M Pelikan)
Jump to: navigation, search
Pelikan
Uetz U3M Pelikan HB-TBV TOU 20.06.65 edited-2.jpg
Uetz U3M Pelikan at Toussus-le-Noble airfield near Paris in June 1965
Role Four-seat cabin monoplane
National origin Switzerland
Manufacturer Walter Uetz Flugzeugbau
Designer Walter Uetz
First flight 21 May 1963
Number built 5
Developed from Uetz U2V

The Uetz Pelikan is a Swiss four-seat cabin monoplane designed for amateur construction by Walter Uetz.

Design and development[edit]

The Pelikan is a four-seat development of the earlier Uetz U2V which had been based on the Jodel D.119.[1] The prototype U3M Pelikan had four-seat cabin with a long transparent canopy.[1] The fixed tail-wheel landing gear U3M is powered by a 135 hp (101 kW) Lycoming O-290 engine and the prototype first flew 21 May 1963, it was followed by a further prototype.[1]

The production variant was designated the U4M which was re-engined with a 150 hp (112 kW) Lycoming O-320-A2B engine and the addition of flaps. The company built two aircraft and one other was amateur-built.[1]

Variants[edit]

U3M Pelikan
Prototype with a 135 hp (101 kW) Lycoming O-290 engine, two built.[1]
U4M Pelikan
Production version with a 150 hp (112 kW) Lycoming O-320-A2B engine, two factory-built and one amateur-built.[1]

Specifications (U4M Pelikan)[edit]

Data from Jane's All The World's Aircraft 1965–66[2]

General characteristics

  • Crew: 1
  • Capacity: 3 passengers
  • Length: 7.50 m (24 ft 7 in)
  • Wingspan: 9.60 m (31 ft 6 in)
  • Height: 2.03 m (6 ft 8 in)
  • Wing area: 13.2 m2 (142 sq ft)
  • Empty weight: 566 kg (1,248 lb)
  • Max takeoff weight: 1,000 kg (2,205 lb)
  • Fuel capacity: 150 L (33 imp gal; 40 US gal)
  • Powerplant: 1 × Lycoming O-320-A2B air-cooled flat-four, 110 kW (150 hp)
  • Propellers: 2-bladed McCauley MGM-7460 fixed pitch

Performance

  • Maximum speed: 219 km/h (136 mph; 118 kn)
  • Cruising speed: 193 km/h (120 mph; 104 kn) (econ cruise)
  • Stall speed: 66 km/h (41 mph; 36 kn)
  • Never exceed speed: 290 km/h (180 mph; 157 kn)
  • Range: 1,000 km (621 mi; 540 nmi) with max fuel
  • Service ceiling: 4,800 m (15,748 ft)
  • Rate of climb: 3.6 m/s (700 ft/min)
  • Take-off run to 15 m (50 ft): 450 m (1,480 ft)
  • Landing run from 15 m (50 ft): 380 m (1,250 ft)

See also[edit]

Related development

References[edit]

Notes[edit]

  1. ^ a b c d e f Simpson 1991, p.364
  2. ^ Taylor 1965, p. 68.

Bibliography[edit]

  • Simpson, R.W. (1991). Airlife's General Aviation. England: Airlife Publishing. ISBN 1-85310-194-X. 
  • Taylor, Jown W. R. (1965). Jane's All The World's Aircraft 1965–66. London: Sampson Low, Marston & Co., Ltd.