Dornier Do-29

The Dornier Do 29 was an experimental aircraft developed by Dornier and the German Aviation Laboratory in the 1950s, It was used to test a tilting-propeller system for short take-off and landing (STOL) aircraft.

Two examples of the Do 29 were constructed, while a third was planned but not built, with the first prototype flying on 12 December 1958.

In the following flight testing, the propeller system was not rotated further than 60 degrees as opposed to its nominal 90 degree capability, but the aircraft proved to be highly successful, with a stalling speed of 24 kilometres per hour (15 mph) and exceptional short-field performance.

Despite this, however, the tilting propeller system was not further pursued after the end of the flight test program.

Specifications

Crew

One 

Length

9.5 m (31 ft 2 in)

Wingspan

13.2 m (43 ft 4 in)

Height

2.69 m (8 ft 10 in)

Wing area

21.8 m2 (235 sq ft)

Empty weight

2,180 kg (4,806 lb)

Gross weight

2,400 kg (5,291 lb)

Max take-off weight

2,490 kg (5,490 lb)

Powerplant

2 × Lycoming GO-480-B1A6 geared horizontally-opposed piston engines, 200 kW (270 hp) each

Propellers

3-bladed

Performance

Maximum speed

290 km/h (180 mph, 160 kn)

Minimum control speed

24 km/h (15 mph, 13 kn)

Range

400 km (250 mi, 220 nmi)

Service ceiling

6,500 m (21,300 ft).