The Dobi-II is the second airplane designed by Lithuanian aviator Jurgis Dobkevičius in 1922. It was tested in October 1923. After two landing accidents plans for mass production of Dobi-II were abandoned. The Dobi-II had long ailerons and were able to be folded due to an internal mechanism. This was most likely done to reduce storage, as the Dobi-II was intended for military usage. During the 1923's the Dobi-II was one of the fastest planes among the two seat aircraft with 200 hp engines. Additionally the hanging control column was used in the Dobi-II.
== Specifications == Data from Lithuanian Air MuseumGeneral characteristics Crew: 2 Length: 6.1 m (20 ft 0 in) Wingspan: 14 m (45 ft 11 in) Wing area: 22.44 m2 (241.5 sq ft) Empty weight: 840 kg (1,852 lb) Gross weight: 1,240 kg (2,734 lb) Powerplant: 1 × Benz Bz.IV 6-cylinder water-cooled inline piston engine, 150 kW (200 hp) Performance
Maximum speed: 248 km/h (154 mph, 134 kn) Cruise speed: 190 km/h (120 mph, 100 kn) Stall speed: 90 km/h (56 mph, 49 kn) Range: 1,000 km (620 mi, 540 nmi) Service ceiling: 9,000 m (30,000 ft) Time to altitude: 34 min to 7,000 m (23,000 ft) Landing speed: 85 km/h (53 mph; 46 kn)
References
See also
Dobi-I Dobi-III